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Full text of "Scout launch vehicle program, phase 6, part 1"

NASA Contractor Report 1 65950, Part 1 

(.iXXia.sbur, .estrone.', ^^5°f\"f?°f* 



X82-103ii6 



) 552 p LIMIT GOVT. 



Wflcias 
B3/15 28726 



SCOUT LAUNCH VEHICLE PROGRAM 
FINAL REPORT - PHASE VI 



Abraham Leiss 




WILLIAMSBURG WEST, INC. 
2013 Cunningham Drive 
Hampton, Virginia 23666 



\ 



4 



«i^ 



Contract NASI -16520 
May 1982 



IWNSA 

National Aeronautics and 
Space Administration 

Langley Research Center 

Hannpton, Virginia 23665 



FOR U.S. 
ONLY 



GOVERNMENT AGENCIES 






X 

TABLE OF CONTENTS 

Page 

LIST OF FIGURES iia 

LIST OF TABLES viii 

LIST OF SYMBOLS AND ABBREVIATIONS xx 

INTRODUCTION xxxi i i 

CHAPTER I - SCOUT LAUNCH VEHICLE PROGRAM ,1 

CHAPTER II - SCOUT LAUNCH VEHICLE HARDWARE 25 

CHAPTER III - PROPULSION kS 

CHAPTER IV - SCOUT LAUNCH VEHICLE SYSTEMS 83 

CHAPTER V - SCOUT RELIABILITY AND Q.UALITY ASSURANCE PROVISIONS ... 99 

CHAPTER VI - SCOUT PROCUREMENT PROGRAM 127 

CHAPTER VII - LAUNCH SITES AND FACILITIES 253 

CHAPTER VIII - SCOUT FINANCIAL DATA 267 

CHAPTER IX - PHASE VI RESULTS 435 

APPENDIXES 

* APPEND IX A - SCOUT PROBE AND REENTRY MISSIONS 515 

*APPENDIX B - SCOUT SINGLE FAILURE POINT INVESTIGATION 527 

*APPENDIX C - SCOUT VEHICLE FAMILY TREE 5^3 

*APPENDIX D - SCOUT PROGRAM REV I EW OF APR I L 5, 1973 569 

*APPENDIX E - TYPICAL SCOUT PREFLIGHT PLANNING REPORT 629 

*APPENDIX F - TYPICAL SCOUT FINAL FLIGHT REPORT 699 

*APPENDIX G - OPERATIONS PLAN 735 

*APPENDIX H - OBLIGATIONS OF FUNDS MEMORANDUM 785 

* APPEND IX I - SCOUT JOB ORDERS 799 

*APPENDIX J - FINANCIAL UPDATE OF PHASES I , I I , AND I I I 835 

*APPENDIX K - FINANCIAL UPDATE OF PHASES IV AND V 869 

**APPENDIX L - DOCUMENTS 893 

**APPENDIX M - BIBLIOGRAPHY 1119 

*Published under separate cover as NASA CR-165950, Part 2 
**Published under separate cover as NASx'V CR-165950, Part 3 



iia 



•*■; 



f 



FIGURE 


NO. 


1 


2 


3 


h 


5 


6 


7 


8 


9 


10 


11 


12 


13 


lif 


15 


16 


17 


18 


19 


20 


21 


22 


23 


2k 



LIST OF FIGURES 

PAGE 
DESCRIPTION NO. 



4 1 Schedule of Scout Program Launches xxxvi 

2 Scout Vehicle S-lBOC Placing CAS-A Into Earth Orbit 2 

Scout Vehicle Growth and Orbital Capabilities k 

Scout-D Launch Vehicle 5 

Scout Vehicle Systems and Structures 6 

S-I9IC Launch Vehicle 7 

Typical Boost Ascent and Payload Injection Into Orbit 9 

Scout Boost Trajectory Pitch Program for Orbit Mission 10 

Typical Scout Orbit Mission Boost Trajectory 10 

Scout-D Circular Orbit Performance I3 

Scout-D Easterly Orbit Capability 14 

Scout-D Polar Orbit Capability I^t 

Elliptical Orbit Performance - Equatorial San Marco Launch. . . I5 

Apogee Altitude - Vandenberg Air Force Base Launch 16 

Scout S-184, First D-1 Using the First Algol MIA Motor .... 17 

Total Scout Geographical Complex 18 

Scout Launch Sites 19 

S-I90 Being Prepared for Launch at San Marco 20 

San Marco Base Camp 21 

1^1 20 Equatorial Launch Complex Showing Platform Blockhouse 21 

Mark II Launcher and Transporter 22 

Mark II Launcher and Transporter, Continued 23 

Sketch of Scout Vehicle (Scout D-1) 27 

Scout Inboard Profile 29 



lib 



LIST OF FIGURES, Continued 

FIGURE PAGE 

NO. DESCRIPTION NO. 

25 Various Station Locations Along the Scout Vehicle 31 

26 Allowable Pay load Weight and C. G. Location 3^ 

27 Pay load Weight Capability of Adapter Sections 35 

28 Scout Heat Shield Data 36 

29 Scout Heat Shield Comparison 37 

30 Scout F-1 Vehicle - Exploded View 39 

31 Launch of S-192 From Western Test Range ^^ 

32 Vehicle Flight Loads Ultimate ^5 

33 Onboard Instrumentation for Loads Experiment on S-133R ^6 

34 Vehicle Ground Handling Loads (Ultimate) ^7 

35 Scout Vehicle Rocket Motor Data 51 

36 Antares Rocket Motor in Test Chamber 55 

37 ANS-A Mission on S-189 Showing Scout Complex at WTR 58 

38 First-Stage Propulsion Unit Used on Scouts A and B 62 

39 First-Stage Propulsion Unit Used on Scouts D and E 63 

kO Scout Second-Stage Propulsion Unit 64 

41 Scout Third Stage 65 

42 Alternate Third Stage 66 

43 Scout-A Fourth Stage 67 

44 X-258 Rocket Motor Data 68 

45 Scouts B Through G Fourth-Stage Propulsion Unit 69 

46 Scout Fifth-Stage Propulsion Unit 70 

47 Five-Stage Scout Payload Envelope 71 

48 Guidance and Controls 85 



I I I 



LIST OF FIGURES, Continued 

FIGURE PAGE 

NO. DESCRIPTION NO. 

kS Location of Controls 86 

50 Second- and Third-Stage Controls 87 

51 Spin Motor Arrangement and Characteristics 87 

52 Spin Rate at Fourth-Stage Ignition and Burnout for Various Roll 

Moments of Intertia 89 

53 Spring Ejection Separation System 90 

5^ Ignition System Block Diagram 92 

55 23-003793 Initiator Assembly 93 

56 Hercules Initiator Assembly Details 93 

57 Destruct System Sk 

58 Scout Vehicle S-110 at k.7 Seconds After Takeoff 95 

59 Simplified Diagram of Instrumentation System 96 

60 Launch of Explorer XIX 101 

61(a) UK-5 Ready for Launch at San Marco 102 

61(b) S-I87 With UK-5 Payload on Launcher at San Marco 102 

62 Scout Fourth-Stage Control Concept Ill 

63 Standard Operating Procedures .... 115 

Sk Detail Schedule - Fourth-Stage ACS 122 

65 Typical Scout Systems Management Contract (NASl-10000) I30 

66 Historical Layout of Scout Contracts 137 

67 Typical Orbit With International Payload (UK-^) S-I83C 138 

68 Scout "G" Section Separation System iBy 

69 Scout Fifth-Stage Layout 190 

70 Scout BE3-A9 Fifth-Stage Motor 191 



IV 



LIST OF FIGURES, Continued 

FIGURE PAGE 

NO. DESCRIPTION NO. 

71(a) Motor Shelflife Summary, 1973 Status 192 

71(b) Motor Shelflife Summary, 1977 Status 192 

71(c) Motor Shelflife Summary, I98O Status 192 

72 Algol MIA Motor Shelf Life 193 

73 Castor III Motor Shelf Life 195 

74 Altair MIA Motor Shelf Life 196 

75 Antares I lA, IMA Shelf Life 197 

76 Scout Logistics Organization Chart 200 

77 Management Organization of Scout Project Office at LaRC . . . 209 

78 LTV Scout Program Management Organization 210 

79 Total Manpower for Scout Program (FY 197^ - 1975) 211 

80(a) Vought Manpower From 196^ Through 1975 212 

80(b) Major Contractor's Manpower From 1964 Through 1975 213 

81 Scout Long Range Mission Scheduling 219 

82 Scout Heat Shield Door Locations 220 

83 Scout Vehicle Furnished Services and Materials for Payload 

Integration 220 

8k Scout Dallas Payload Processing 227 

85 Scout Payload Vibration Testing Sinusoidal Levels 228 

86 Scout Payload Vibration Testing Random Levels 229 

87 Integrated Field Schedule 23^ 

88 Scout Shipping Expenditures 2^9 

89 Contract Task Designation 251 

90 Scout Launch Facility at Wallops Flight Center 25^ 



FIGURE 


NO. 


91 


92 


93 


Sk 


95 


96 


97 


98 


99 


100 


101 


102 


103 


104 


105 


106(a) 


106(b) 


107 


108 


109(a) 


109(b) 


109(c) 


110 



V 

LIST OF FIGURES, Continued 

PAGE 

DESCRIPTION NO. 

Sketch of Wallops Island Launch Complexes 256 

Sketch of Western Test Range Launch Site 257 

Wallops Island Launch Complex Blockhouse Consoles 258 

Movable Shelter Exterior - Typical 259 

Movable Shelter Interior - Typical 259 

Range Users Building, WTR 260 

Spin Test Facility - WTR 260 

Assembly Building - Wallops Island 261 

Telemetry Mobile Ground Station (T/M Van) 262 

Fueling Room Servicing Equipment - Typical 262 

Vehicle Assembly Area - Dallas 263 

Pay load Field Flow Processing Plan 264 

Scout Mark- 1 I Launcher at Wallops Island 265 

Lift-off of S-181 Which Placed AEROS-A Into Orbit 266 

Contract NASl-5610 Proration of Costs 361 

Contract NASI -6020 Proration of Costs 362 

Contract NASl-6020 Proration of Costs, Continued 363 

Contract NASI -6935 Proration of Costs 364 

Contract NAS1-7199 Proration of Costs 365 

Contract NASI -7256 Proration of Costs 366 

Contract NASl-7256 Proration of Costs, Continued 367 

Contract NASl-7256 Proration of Costs, Concluded 368 

Contract NASI -10000 Proration of Costs 369 



VI 



LIST OF FIGURES, Continued 

FIGURE PAGE 

NO. DESCRIPTION NO. 

111(a) Contract NASl-10000 Proration of Costs 370 

111(b) Contract NASl-10000 Proration of Costs, Continued 371 

111(c) Contract NASl-10000 Proration of Costs, Continued 372 

112 Proration of Other Contracts (^90 Funds Only) 373 

113 Phase Vl R & D - Propulsion Prorations 373 

114 Contract NASI -11400 Proration of Costs 374 

115 Contract NASl-12500 Proration of Costs 375 

116 Contract NASI -14200 Proration of Costs 376 

117 Contract NAS1-15000 Proration of Costs 376 

118 Contract NAS1-15100 Proration of Costs 377 

APPENDIXES 

A-1 Typical Probe Ascent Trajectory 519 

A-2 Probe Performance - Apogee Altitude 520 

A-3 Probe Performance - Time at Zero "g" 521 

A-4 Solar Probe Performance 522 

A-5 Typical Reentry Profile With Stage Impacts 524 

A-6 Reentry Performance at Fourth-Stage Burnout 525 

B-1 Basic Logic Gates 53*+ 

B-2 Special Logic Gates 535 

B-3 Event Representations 535 

B-4 Transfer Symbol 536 

B-5 Hypothetical System 536 

B-6 Fault Tree 539 



VM 

LIST OF FIGURES, Concluded 
APPENDIX 
FIGURE 

NO. DESCRIPTION 

C-Diagrams List of Diagrams 

E-Figures List of Figures 

F-Figures List of Figures 

G-2 Figures List of Figures 

L-Figures List of Figures 



PAGE 
NO. 

547 
636 
706 
762 
895 



,«^ 



VM I 



LIST OF TABLES 



TABLE 




NO. 




1 
1 1 




1 II 




IV 




V 




VI 




VII 




VIM 




IX 




X 




XI 




XII 




XIII 




XIV 




XV 




XVI 




XVII 




XV III 




XIX 




XX 




XXI 




XXI 1 




XXII 1(a) 


XXI It 


(b) 



PAGE 

DESCRIPTION NO. 

DESIGNATION OF SCOUT CONFIGURATIONS 3 

SEaUENCE OF EVENTS AND GUIDANCE PROGRAM 11 

SCOUT STAGES 28 

BASE AND TRANSITION SECTION COMPOSITION 31 

NOMINAL VEHICLE WEIGHTS, SCOUT A-1 kO 

NOMINAL VEHICLE WEIGHTS, SCOUT B-1 ^1 

NOMINAL VEHICLE WEIGHTS, SCOUT D-1 ^2 

NOMINAL VEHICLE WEIGHTS, SCOUT E-1 ^3 

ROCKET MOTOR PHYSICAL DATA 50 

ROCKET MOTOR PERFORMANCE DATA 52 

MOTOR SHELF LIFE SUMMARY 58 

HISTORY OF MOTORS AND HEAT SHIELDS, PHASES I , I I , AND I 1 I . . 59 

HISTORY OF MOTORS AND HEAT SHIELDS, PHASES IV AND V 60 

MOTORS ASSIGNED TO PHASES VI AND VII 61 

INVENTORY BALANCE OF PHASES V I I AND V I I I 61 

AEROJET MOTOR HISTORY. . 72 

UNITED TECHNOLOGY MOTOR HISTORY, ALGOL III 73 

THIOKOL MOTOR HISTORY, CASTOR I 7^ 

THIOKOL MOTOR HISTORY, CASTOR II 75 

HERCULES MOTOR HISTORY, ANTARES MA 76 

THIOKOL MOTOR HISTORY, ANTARES MA AND MB 77 

THIOKOL MOTOR HISTORY, ANTARES IMA 77 

HERCULES MOTOR HISTORY, ALTAIR II 78 

HERCULES MOTOR HISTORY, ALCYONE (BE3-A9) 79 



IX 



LIST OF TABLES, Continued 

TABLE PAGE 

NO. DESCRIPTION nq, 

XXIV UNITED TECHNOLOGY MOTOR HISTORY (ALTAIR IMA) 80 

XXV THIOKOL (ELKTON) TEM-640 ALTAIR IMA HISTORY 8l 

XXVI GUIDANCE AND CONTROLS DATA 88 

XXVII ASSESSED DESIGN GOALS FOR SCOUT SYSTEMS 104 

XXVIII COMPONENT DATA IO7 

XXIX COMPONENT FLIGHT ACCEPTANCE TEST DATA IO8 

XXX SCOUT FIELD QUALITY AND RELIABILITY PROGRAM 114 

XXXI MAJOR R&D IMPROVEMENTS TO ORIGINAL SCOUT 11 7 

XXXII SCOUT VEHICLE PROCUREMENTS, PHASES I THROUGH VI 129 

XXXIII SUMMARY OF SCOUT CONTRACTS I3I 

XXX IV (a) SUMMARY OF SCOUT CONTRACTS (1972-1979 134 

XXXIV(b) SUMMARY OF SCOUT CONTRACTS INCLUDED IN PHASE V (PRIOR TO 1972) 135 

XXXV SUMMARY OF PHASE VI VEHICLE CONTRACTS I36 

XXXVI SUMMARY OF SOFTWARE CONTRACTS FOR EACH PHASE VI SCOUT VEHICLE. I36 

XXXVII SCOUT - NASI-56IO (CONTRACT HISTORY) 139 

XXXVIII SCOUT - NASI -6020 (CONTRACT HISTORY) 142 

XXXIX SCOUT - NASI-7IO2 (CONTRACT HISTORY) 147 

XL SCOUT - NA.Sl-7199 (CONTRACT HISTORY) 148 

XL I SCOUT - NASI -7256 (CONTRACT HISTORY) I5I 

XLII SCOUT - NASl-9258 (CONTRACT HISTORY) 155 

XLIM SCOUT - NAS1-10000 (CONTRACT HISTORY) 157 

XLIV SCOUT - NAS1-11400 (CONTRACT HISTORY) I63 

XLV SCOUT - NASI -12500 (CONTRACT HISTORY) I67 

XLVI SCOUT - NASI -131 00 (CONTRACT HISTORY) 172 



LIST OF TABLES, Continued 

TABLE PAGE 

NO. DESCRIPTION NO. 

XLVII SCOUT - NAS1-42000 (CONTRACT HISTORY) 17^ 

XLVIII SCOUT- NASI-I5OOO (CONTRACT HISTORY) 178 

XLIX SCOUT - NASl-15100, TASK R SPECIAL STUDIES 182 

L SOLID PROPULSION AND PYROTECHNIC SHELF LIFE AND AGING PROGRAM 

OBLIGATIONS 198 

LI (a) SUMMARY OF SERVICES, NASI -10000 204 

Ll(b) SUMMARY OF SERVICES, NASI -12500 205 

Lll(a) DETAILS OF SERVICES, NASl-10000 206 

LI 1(b) DETAILS OF SERVICES, NASl-12500 207 

LI II MANUFACTURING PERSONNEL REQUIRED FOR VEHICLE PROCESSING ... 214 

LIV MANPOWER LIST (PLAN "B") 217 

LV SCOUT PROJECT PAY LOAD COORDINATION PLAN 222 

LVI NASl-10000 R-TASKS 238 

LVII NASl-12500 R-TASKS 240 

LVI I I NASl-10000 S-TASKS 243 

LIX NASl-12500 S-TASKS 245 

LX GOVERNMENT FURNISHED GROUND SUPPORT EQUIPMENT 245 

LXI FACILITIES 255 

LXII HISTORY OF SCOUT FUNDS, BY PHASES 269 

LXI II SCOUT FUNDS BY FISCAL YEAR 271 

LXIV(a) SUMMARY OF SCOUT NASA, AEC , AND DOD PROGRAMS 272 

LXIV(b) SCOUT PROGRAM R&D OBLIGATIONS 273 

LXIV(c) SCOUT PROGRAM R&D OBLIGATIONS 274 

LXIV(cl) SCOUT PROGRAM R & D OBLIGATIONS 275 



XI 



.( * 



TABLE 
NO. 

LXV(a) 

LXV(b) 

LXV(c) 

LXVI 

LXVII 

LXVI I 

LXVII 

LXVII 

LXVI I 

LXVI I 

LXVI I 

LXVII 

LXVII 

LXVII 

LXVI 1 

LXVII 

LXVI I 

LXV I I 

LXVII 

LSVII 

LXIX 

LXX 

LXXI 

LXX I I 



LIST OF TABLES, Continued 
DESCR I PT I ON 



OBLIGATION OF FUNDS BY VEHICLE 

PHASE VI OBLIGATION OF FUNDS BY VEHICLE - NASA, 
PHASE VI OBLIGATION OF FUNDS BY VEHICLE - DOD . 

PHASE VI HARDWARE OBLIGATIONS 

SUMMARY OF PHASE VI OBLIGATIONS BY TASKS (490). 



(a) VEHICLE S-I78 OBLIGATIONS 

(b) VEHICLE S-179 OBLIGATIONS 

(c) VEHICLE S-I8O OBLIGATIONS 

(d) VEHICLE S-181 OBLIGATIONS 

(e) VEHICLE S-lBZ OBLIGATIONS 

(f) VEHICLE S-I83 OBLIGATIONS 

(g) VEHICLE S-184 OBLIGATIONS 
(h) VEHICLE S-I85 OBLIGATIONS 
(i) VEHICLE S-186 OBLIGATIONS 
(j) VEHICLE S-I87 OBLIGATIONS 
(k) VEHICLE S-188 OBLIGATIONS 
(1) VEHICLE S-I89 OBLIGATIONS 
(m) VEHICLE S-190 OBLIGATIONS 
(n) VEHICLE S-191 OBLIGATIONS 
(o) 



(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 

(MAJOR CONTRACTS 



VEHICLE S-192 OBLIGATIONS 

PHASE VI SUSTAINING EFFORT BY MAJOR CONTRACTS 

SCOUT PROGRAM FY 1972 OBLIGATIONS 

SCOUT PROGRAM FY 1973 OBLIGATIONS 

SCOUT PROGRAM FY 197^ OBLIGATIONS 



BY TASKS, 
BY TASKS. 
BY TASKS, 
BY TASKS, 
BY TASKS. 
BY TASKS. 
BY TASKS. 
BY TASKS. 
BY TASKS. 
BY TASKS. 
BY TASKS, 
BY TASKS, 
BY TASKS, 
BY TASKS, 
BY TASKS, 



PAGE 
NO. 

276 

277 

278 

279 

280 

281 

282 

283 

284 

285 

286 

287 

288 

289 

290 

291 

292 

293 

294 

295 

296 

297 
300 

303 



XI I 



TABLE 


NO. 


LXX 1 1 1 


LXXIV 


LXXV 


IXWI 


LXXV 1 1 


LXXV II 1 


LXX IX (a) 


LXXIX(b) 


LXX IX (c) 


LXXIX(d) 


LXXIX(e) 


LXXIX(f) 


LXXIX(g) 


LXXX 


LXXXI 


LXXX 1 1 


LXXXI II 


LXXX IV 


LXXXV 


LXXXV 1 


LXXXV II 


LXXXV 1 1 1 


LXXX IX 



LIST OF TABLES, Continued 



DESCRIPTION 



PAGE 
NO. 



SCOUT PROGRAM FY 1975 OBLIGATIONS 306 

SCOUT PROGRAM FY 1976 OBLIGATIONS 309 

SCOUT PROGRAM FY 197T OBLIGATIONS 312 

SCOUT PROGRAM FY 1977 OBLIGATIONS 316 

SCOUT PROGRAM FY 1978 OBLIGATIONS 319 

SCOUT PROGRAM FY 1979 OBLIGATIONS 32k 



FY 1961 NASA PRODUCTION (490 
FY 1962 NASA PRODUCTION (490 
FY 1963 NASA PRODUCTION (490 
FY 1964 NASA PRODUCTION (490 
FY 1965 NASA PRODUCTION (490 
FY 1966 NASA PRODUCTION (490 
FY 1967 NASA PRODUCTION (490 
FY 1968 NASA PRODUCTION (490 
FY 1969 NASA PRODUCTION (490 
FY 1970 NASA PRODUCTION (490 
FY 1971 NASA PRODUCTION (490 
FY 1972 NASA PRODUCTION (490 
FY 1973 NASA PRODUCTION (490 
FY 1974 NASA PRODUCTION (490 
FY 1975 NASA PRODUCTION (490 
FY 1976 NASA PRODUCTION (490 
FY 197T NASA PRODUCTION (490 



OBLIGATIONS 329 

OBLIGATIONS 329 

OBLIGATIONS 329 

OBLIGATIONS 329 

OBLIGATIONS 330 

OBLIGATIONS 330 

OBLIGATIONS 330 

OBLIGATIONS 331 

OBLIGATIONS 331 

OBLIGATIONS 333 

OBLIGATIONS 335 

OBLIGATIONS 337 

OBLIGATIONS 339 

OBLIGATIONS 341 

OBLIGATIONS 343 

OBLIGATIONS 344 

OBLIGATIONS 346 



X I M 



LIST OF TABLES, Continued 

TABLE PAGE 

NO. DESCRIPTION NO. 

XC FY 1977 NASA PRODUCTION (490) OBLIGATIONS Ikl 

XCI FY 1978 NASA PRODUCTION (^90) OBLIGATIONS 348 

XCII FY 1979 NASA PRODUCTION (490) OBLIGATIONS 349 

XCI I I (a) SCOUT - AIR FORCE FY 1962 OBLIGATIONS 350 

XCI I 1(b) SCOUT - AIR FORCE FY 1963 OBLIGATIONS 350 

XCI I 1(c) SCOUT - AIR FORCE FY 1964 OBLIGATIONS 350 

XCIV scour - AIR FORCE FY 1 965 OBLIGATIONS 350 

XCV SCOUT - AIR FORCE FY I966 OBLIGATIONS 350 

XCVI SCOUT - AIR FORCE FY I967 OBLIGATIONS 351 

XCVII SCOUT - AIR FORCE FY I968 OBLIGATIONS 352 

XCVI I I SCOUT - AIR FORCE FY 1969 OBLIGATIONS 354 

XCIX SCOUT - AIR FORCE FY 1970 OBLIGATIONS 354 

C SCOUT - AIR FORCE FY 1971 OBLIGATIONS 354 

CI SCOUT - AIR FORCE FY 1972 OBLIGATIONS 355 

CM SCOUT - AIR FORCE FY 1973 OBLIGATIONS 356 

cm SCOUT - AIR FORCE FY 1974 OBLIGATIONS 356 

CIV SCOUT - AIR FORCE FY 1975 OBLIGATIONS 357 

CV SCOUT - AIR FORCE FY 1976 OBLIGATIONS 357 

CVI SCOUT - AIR FORCE CY 1977 OBLIGATIONS 358 

Cvii TOTAL PHASE VI (490) OBLIGATIONS. = , - 359 

CVI I I FOREIGN REIMBURSABLE AUTHORITY 377 

CIX TRUST FUNDS 377 

CX ESRO-IB FINAL COSTS 378 



XIV 



TABLE 


NO. 


CXI 


CXIl 


CXI II 


CXIV 


CXV 


CXVI 


CXV II 


CXVI II 


CXIX 


CXX 


CXXI 


CXXI 1 


CXXI 1 1 


CXXIV 


CXXV 


CXXVI 


CXXV II 


CXXVI II 


CXX IX 


cxxx 


CXXXl(a) 


cxxx 1(b) 


cxxx 1(c) 



LIST OF TABLES, Continued 

PAGE 

DESCRIPTION NO. 

ESRO-IV FINAL COSTS 379 

AEROS-B FINAL COSTS 380 

UK-X'+ FINAL COSTS 381 

UK-5 REIMBURSABLE EXPENDITURES 382 

UK-6 MAY 1, 1980 ESTIMATED COSTS 384 

SCOUT UK-6 MISSION 385 

SAN MARCO SUPPORT, TASK J TO CONTRACT NASI -10000 386 

SAN MARCO SUPPORT, TASK J TO CONTRACT NASI -12500 38? 

EXHIBIT - TYPICAL EXAMPLE OF U.S. REPORT TO ITALY ON SAN 

MARCO "C" 388 

SAN MARCO "D" DEPOSIT ACCOUNT 392 

DOD EXPENDITURES 39^+ 

DOD COST SUMMARY 395 

SCOUT 66-95 PROGRAM, PER-LAUNCH COST 395 

SCOUT 66-95 PROGRAM COSTS (ESTIMATED) PHASES IV 6- V ANNUAL 

COSTS 396 

SCOUT 68-71 PLANNED PROGRAM ESTIMATES 397 

SCOUT 68-71 PLANNED PROGRAM ESTIMATES, PHASES VI & VII ... • 398 

DOD/SCOUT 68-71 SUMMARY THROUGH 1979 399 

COST ESTIMATES FOR P76-5 (S-179) ^°° 

VAFB REIMBURSABLE SERVICES ^0^ 

VAFB UTILITY COSTS ^02 

SCOUT E-SECTIONS ^03 

SCOUT E-25 SECTIONS ^0^ 

SCOUT E-G SECTIONS . ^0^ 



XV 



TABLE 
NO. 

CXXXl(cl) 

CXXXl(e) 

CXXXI 1(a) 

CXXXI 1(b) 

CXXX I I I 

CXXXIV 

CXXXV(a) 

CXXXV(b) 

CXXXVI 

CXXXVI I 

CXXXVI 11(a) 

CXXXVI 11(b) 

CXXXVI I 1(c) 

CXXX IX 

CXL 

CXLl(a) 

CXLI (b) 

CXLI I 

CXLI I I 

CXLIV 

CXLV 

CXLVI 

CXLV I I 

CXLVI I I 



LIST OF TABLES, Continued 

PAGE 

DESCRIPTION NO. 

SCOUT G-SECTIONS /^04 

SCOUT E- AND G-SECTIONS PROCUREMENT Z^OS 

3^- INCH HEAT SHIELDS Z^OS 

42- INCH HEAT SHIELDS 2+07 

TASK M -(01) PER VEHICLE LOGISTICS COSTS, NASI -12500/1 5100. . 408 

TYPICAL ANALYSIS OF TASK T USING TASK T OF NASl-15000 .... iflO 

PRORATION OF NASl-12500 TASK N 411 

PRORATION OF NASl-12500 TASK N, Continued 412 

TASK N - FIELD TEAM SUMMARY 41 3 

RANGE OPERATIONS AND MAINTENANCE EXPENDITURES, VAFB 41 4 

MSO-WTR EXPENDITURES 41 7 

MSO-WTR EXPENDITURES SUMMARY SHEET, FY 1977 418 

MSO-WTR EXPENDITURES SUMMARY SHEET, FY 1978 419 

GSE EXPENDITURES 420 

DOD PLANT SERVICES 421 

SCOUT SHIPPING EXPENDITURES 422 

SCOUT SHIPPING EXPENDITURES, Concluded 423 

IMPROVEMENTS - PHASE VI (S-I78 THRU S-192) 424 

SRT (STO) RESEARCH PROGRAMS (I8O FUNDS) 425 

NASI -10481 CONTRACT HISTORY 426 

NASI -10482 CONTRACT HISTORY 427 

NASI -10483 CONmACT HISTORY 428 

NASI -10484 CONmACT HISTORY 429 

NASI -10500 CONTRACT HISTORY 430 



XVI 



LIST OF TABLES, Continued 

TABLE PAGE 

NO. DESCRIPTtON NO. 

CXLIX NASl-12500, NAS1-15000, AND NASl-15100 STANDARD TASKS ^31 

CL NASl-12500, NASI-I5OOO, AND NASl-15100 STANDARD TASKS (68-71). • ^32 

CLI NASl-12500 AND NASl-15100 - DOD TASK R (68-71) SPECIALS ^33 

CLII NASl-12500 AND NASl-15100 - DOD TASK R (68-71) SHELFLIFE .... 433 

CLI I I (a) SUMMARY OF RESULTS (PHASES I, II, AND III) ^37 

CLI I 1(b) SUMMARY OF RESULTS (PHASES IV AND V) 438 

CLIV LAUNCH SUMMARY (PHASE VI) 439 

CLV SCOUT FLIGHT SUMMARY (OPERATIONAL) 440 

CLVI POSTFLIGHT SUMMARY, SCOUT S-I78C 449 

CLVII POSTFLIGHT SUMMARY, SCOUT S-1 79C 450 

CLVI I I POSTFLIGHT SUMMARY, SCOUT S-I8OC 451 

CLIX POSTFLIGHT SUMMARY, SCOUT S-1 81 C 452 

CLX POSTFLIGHT SUMMARY, SCOUT S-182C 453 

CLXI POSTFLIGHT SUMMARY, SCOUT S-I83C 454 

CLXII POSTFLIGHT SUMMARY, SCOUT S-184C 455 

CLXI I I POSTFLIGHT SUMMARY, SCOUT S-I85C 456 

CLX IV POSTFLIGHT SUMMARY, SCOUT S-I86C 457 

CLXV POSTFLIGHT SUMMARY, SCOUT S-I87C 458 

CLXVI POSTFLIGHT SUMMARY, SCOUT S-I88C 459 

CLXVII POSTFLIGHT SUMMARY, SCOUT S-189C 460 

CLXVI I I POSTFLIGHT SUMMARY, SCOUT S-I9OC 461 

CLXiX POSTFLIGHT SUMMARY, SCOUT S-I9IC 462 

CLXX POSTFLIGHT SUMMARY, SCOUT S-192C 463 



XVI I 



LIST OF TABLES, Continued 

TABLE PAGE 

NO. DESCRIPTION NO. 

CLXXI SUMMARY OF BOOST TRAJECTORY FOR S-I78 kSh 

CLXXII SUMMARY OF BOOST TRAJECTORY FOR S-179 kSS 

CLXXI I I SUMMARY OF BOOST TRAJECTORY FOR S-I8O 466 

CLXXIV SUMMARY OF BOOST TRAJECTORY FOR S-I8I 467 

CLXXV SUMMARY OF BOOST TRAJECTORY FOR S-182 468 

CLXXVI SUMMARY OF BOOST TRAJECTORY FOR S-I83 469 

CLXXVII SUMMARY OF BOOST TRAJECTORY FOR S-184 470 

CLXXVI I I SUMMARY OF BOOST TRAJECTORY FOR S-185 471 

CLXXIX SUMMARY OF BOOST TRAJECTORY FOR S-186 472 

CLXXX SUMMARY OF BOOST TRAJECTORY FOR S-I87 473 

CLXXXI SUMMARY OF BOOST TRAJECTORY FOR S- 188 474 

CLXXXII SUMMARY OF BOOST TRAJECTORY FOR S-I89 475 

CLXXXI I I SUMMARY OF BOOST TRAJECTORY FOR S-190 476 

CLXXXIV SUMMARY OF BOOST TRAJECTORY FOR S-191 477 

CLXXXV PITCH ATTITUDE ERRORS - SCOUTS 186 THROUGH I89 478 

CLXXXVI PITCH ATTITUDE ERRORS - SCOUTS I78, 190, 191 479 

CLXXXVII ROLL ATTITUDE ERRORS - SCOUTS 186 THROUGH I89 480 

CLXXXVIII ROLL ATTITUDE ERRORS - SCOUTS 190, 191, 178 481 

CLXXX IX YAW ATTITUDE ERRORS - SCOUTS 177, 178, I80 482 

CXC YAW ATTITUDE ERRORS - SCOUTS 181 THROUGH 1 85 483 

CXCI YAW ATTITUDE ERROR - SCOUTS 166 THROUGH iSy 484 

CXCII ROLL ATTITUDE ERROR - SCOUTS 190, 191 485 

CXCI I I FIRST STAGE PITCH PROGRAM 486 



XVI M 



TABLE 
NO. 

CXCIV 

CXCV 

CXCVI 

CXCV I I 

CXCV I I I 

CXCIX 

CC 

CCI 

ecu 

CCI il 

CCIV 

CCV 

CCVI 

CCV I I 

CCVI I I 

CCIX 

CCX 
CCXI 
CCX I I 
CCXI II 
CCXIV 

ccxv 



LIST OF TABLES, Continued 

PAGE 

DESCRIPTION NO. 

FIRST STAGE MOMENT OF DISTURBANCES, S-178C ^7 

FIRST STAGE MOMENT OF DISTURBANCES, S-I8OC ^8 

FIRST STAGE MOMENT OF DISTURBANCES, S-I8IC ^89 

FIRST STAGE MOMENT OF DISTURBANCES, S-182C ^90 

FIRST STAGE MOMENT OF DISTURBANCES, S-I83C ^91 

FIRST STAGE MOMENT OF DISTURBANCES, S-184C 492 

FIRST STAGE MOMENT OF DISTURBANCES, S-I85C 493 

FIRST STAGE MOMENT OF DISTURBANCES, S-I86C 494 

FIRST STAGE MOMENT OF DISTURBANCES, S-187C 495 

FIRST STAGE MOMENT OF DISTURBANCES, S-I88C 496 

FIRST STAGE MOMENT OF DISTURBANCES, S-I89C 497 

FIRST STAGE MOMENT OF DISTURBANCES, S-190C 498 

FIRST STAGE MOMENT OF DISTURBANCES, S-191C 499 

SCOUT SECOND STAGE INITIAL CONDITIONS AND CAPTURE 500 

SCOUT THIRD STAGE INITIAL CONDITIONS AND CAPTURE 501 

PITCH AND YAW MOMENTS AND THRUST MISALIGNMENTS, SCOUT SECOND 

AND THIRD STAGES 502 

SCOUT TOTAL THRUST MISALIGNMENT VS TIME 503 

SCOUT TOTAL THRUST MISALIGNMENT VS TIME, Continued 504 

SCOUT SECOND STAGE (CASTOR II) THRUST MISALIGNMENT VS TIME. . 505 

SCOUT THIRD STAGE (ANTARES ilA) THRUST MISALIGNMENT VS TIME . 506 

SCOUT SECOND STAGE FUEL CONSUMPTION REACTION CONTROL SYSTEM . 507 

SCOUT THIRD STAGE FUEL CONSUMPTION REACTION CONTROL SYSTEM. . 508 



XIX 



LIST OF TABLES, Concluded 

TABLE PAGE 

NO. DESCRIPTION NQ. 

CCXVI SCOUT FIRST STAGE MOTOR PERFORMANCE SUMMARY 509 

CCXVII SCOUT SECOND STAGE MOTOR PERFORMANCE SUMMARY 5IO 

CCXVI I I SCOUT THIRD STAGE MOTOR PERFORMANCE SUMMARY 51 1 

CCXIX SCOUT FOURTH STAGE MOTOR PERFORMANCE SUMMARY 512 

CCXX SCOUT SUMMARY OF DYNAMIC RESPONSE DATA 5I3 

APPENDIXES 

B-1 CRITICAL FUNCTIONS LIST - PRELAUNCH 53I 

B-ll CRITICAL FUNCTIONS LIST- FLIGHT 532 

C-CHARTS TABLE OF CONTENTS (Block Diagrams) 5if7 

C-R PAYLOAD INTERFACE DRAWING LIST 566 

C-S MODIFICATION ACCUMULATION DRAWINGS 567 

E-TABLES LIST OF TABLES 635 

F-TABLES LIST OF TABLES 7O6 

G-2 SCOUT 188 OPERATIONS SUMMARY LIST OF TABLES 762 

J-TABLES FINANCIAL UPDATE OF SCOUT PHASES I, II, & III TABLES .... 838 

K-TABLES FINANCIAL UPDATE OF SCOUT PHASES IV AND V TABLES 872 

L- TABLES LIST OF TABLES 895 



XX 



LIST OF SYMBOLS AND ABBREVIATIONS 



A 

A - Z 

ALERTS 

kk - 11 

AAA - 111 

A - G 

A— ^G 

A - M 

ABL 

Abs. 

AC 

ACS 

ACS 

Add. 

AD/I-C 

AD IE 

ADL 

Admin i s . 

AEC 

A.E.C. 

AEDC, A.E.D.C. 

AEM 

AEROS 

AF, A.F. 

AFB 

AFSC 

AFWTR 

AGC 

AGE 

A-IQSY 

AL 

Alg. 

ALT. 

AMM. 

Anal . 

AN/FPS 

ANS 

AN/MPS 

Approx. 

ARIEL 

ASTVg. 

atch. Hdwe. 

A.U. 

AZ 

AZUR 

609A 

ATJ-S 

AN/FRW 



Army 

Task and Job Order Designations 

Industrywide Failure Reports Initiated by GIDEP 

Scout Task Codes 

DITTO 

Vehicle Configurations 

Vehicle Section Designations 

Appendix Designations for This Report 

Allegany Ballistics Laboratory 

Absolute 

Alternating Current 

Attitude 

Automatic Control System 

Additional 

Air Density No. 1-C 

Air Density Instrument Experiment 

Administrative Direct Line 

Admini strati on 

Atomic Energy Commission 

DITTO 

Arnold Engineering Development Center 

Applications Energy Missions 

German Satel 1 i te 

Air Force 

Air Force Base 

Air Force Systems Command 

Air Force Western Test Range 

Aerojet General Corporation 

Aerospace Ground Equipment 

NRL Solar Explorer Satellite 

Atomic Energy Commission Special Funds 

Algol 

Altitude 

Ammun it ion 

Analys is 

Radar System 

Astronomical Netherlands Satellite 

Radar System (Module MPS-26) 

Approximately 

United Kingdom Satellite 

Air Force Space Test Wing 

Attachment Hardware 

Astronimical Unit 

Azimuth 

German Satel 1 i te 

Air Force Blue Scout Program 

Type of Graphite in Initiators 

Range Safety Transmitter (Command Destruct) 



XXI 



SYMBOLS AND ABBREVIATIONS Continued 



B/A 


Base-A Section 


BATT. 


Battery 


BE 


Beacon Explorer 


BE3A9 


Fifth-Stage Motor Designation 


BKNO 


Igniter Pellets 


BPDAD 


SAMTEC NOVA Job Order Designation 


B/U 


Build Up 


C 


Certified 


CA 


Call (Contractual) 


CART. 


Cartridge 


Cas 


Castor 


CAS 


Cooperative Applications Satellite 


C-Band 


Radio Frequency Range 


CCF 


Component Cleaning Facility 


CCN 


Contract Change Notice 


CCTV 


Pan Tilt Heads 


CCW 


Counter Clockwise 


C/F, C of F 


Construction of Facilities 


C.G. 


Center of Gravity 


Chmb. 


Chamber 


CHG., chng. 


Changes 


CIR. , cir. 


Circuits 


C/O 


Checkout 


Comp. 


Components 


Comp. 


Compos i te 


Complet 


Complet ion 


Cont. 


Control 


CPFF 


Cost Plus Fixed Fee 


C.R. 


Cost Reimbursable 


C.R. 


Contractor's Report 


CRA 


Centro Ricerche Aerospaziali 


Cse. 


Case 


Cs. P/Fit 


Case Pole Fitting 


CTM 


FM/FM Transmitter 


CTM/UHF 


Telemetry Transmitter 


CTR 


Center 


CW 


Clockwise 


DAD 


Dual Air Density 


DAL 


Dal las 


db 


Decibel 


DCA50 


Defense Contract Audit Service Organization 


DC 


Direct Current 


DEG, deg. 


Degrees 


DEMO 


Demonstration 


Dept. 


Department 


Des., Desn. 


Des ign 



XXI I 



SYMBOLS AND ABBREVIATIONS Continued 

DEST. Destruct 

Dev. Development 

Dia, DIA Diameter 

DIR Design Information Release 

Div. Division 

Dnj Down 

DOD Department of Defense 

D.O.F. Degree of Freedom 

DR Drawing 

DSA Defense Supply Agency 

DTD Dated 

Dwgs. Drawings 

DWI's Daily Work Items 

E E Separation System 

EAR & T East African Post and Telecommunication 

ECS Environmental Control System 

EDT Eastern Daylight Time 

E-G E-G Separation System 

EGSE Electrical Ground Support Equipment 

ELEC. Electrical 

Emerg. Emergency 

E.G. Engineering Order 

EOLE French Satel 1 i te 

ERNO European Research Organization 

ESA European Space Administration 

ESRO European Space Research Organization 

EVAL., EV. Evaluation 

EX Explorer 

EXP Explorer 

EXP. Expense 

EXT., Extens. Extend, Extension 

Engr. Engineering 

F Failure 

F Fahrenheit 

Fab. Fabrication, Fabricate 

FAIL. Failure 

FFP Firm Fixed Price 

Fit. Flight 

FM Frequency Modulation 

F.P.I. Fixed Price Incentive 

F.P.I. A. Fixed Price Incentive Award 

FPQ Radar 

FPS Radar System 

fps, FPS Feet Per Second 

FS Feasibi 1 i ty Study 

ft. Feet 

ft. /sec. Feet Per Second 

FT- LBS Foot Pounds 



XXI I I 



SYMBOLS AND ABBREVIATIONS Continued 



FUNDS 
FW-^S 
FY 



Agency and Fiscal Year 
Fourth-Stage Motor 
Fiscal Year 



Fund Code (See Page 



g 

G 

G & A 

GBL 

GFE 

GFP 

G/Hz 

GIDEP 

G.M.T. 

GRP 

GSA 

GSE 

GSFC 

Guid. 

HA 

HAAP 

HCMM 

Hdcp. 

Hdwr. 

HE 

H.E.P., HEP 

HF 

Hg 

HI 

HIB 

H2O2 

HP 

HPC 

Hq., HQ.. 

H.S., H/S 

HSD 

HTC 

HTPB 



Ign. 

IGN 

IKS 

jmn _ 

IMS 
in. , 
Inc. 
incl . 
Incorp 



IN 



Acceleration 

Separation System 

General and Administrative 

Government Bill of Lading 

Government Furnished Equipment 

Government Furnished Property 

Acceleration Density 

Government/ I ndustry Data Exchange Program 

Greenwich Mean Time 

German Probe 

General Services Administration 

Ground Support Equipment 

Goddard Space Flight Center 

Gu idance 

High Altitude 

Huntsvi 1 le Army 

Heat Capacity Mapping Mission 

Headcap 

Hardware 

High Energy 

High Energy Propulsion 

High Frequency 

Mercury 

Hercules, Incorporated 

Hercules, Incorporated/Bacchus Plant 

Hydrogen Peroxide 

High Pressure 

Hercules Powder Company 

Headquarters 

Heat Shield 

Hawker Siddeley Dynamics 

Hampton Technical Center 

Hydroxyl Terminated Polybutadiene 

Igniter 

Ignition 

Spin Motor 

Improvement 

Institutional Management System 

I nches 

Include 

Incl inat ion Angle 

I ncorporated 



XXIV 



INS 

Inspt. 

Insul . 

Invest. 

IRiG 

IRP 

ISC 



sp 



It 
ITEM 

OTT- 1 N645 

J.O. 
JPGEN 

Kd 

KG 

KHz 

Km 

Km/Sec 

Kr/Kd 

KSC 

kw 



SYMBOLS AND ABBREVIATIONS Continued 

Improved Navy Satellite 

Inspect ion I nstru. Instrumentation 

Insulation 

Invest igat ion 

International Range Instrumentation Guide 

Instrumented Research Package 

Italian Space Commission 

Specific Impulse, sec. 

Total Impulse, LB-SEC. 

Compute Code Number at LRC. 

Electronic Diode 

Job Order 
Generator 

Displacement Gain deg/deg 

Ki log ram 

Ki lohertz 

Ki lometer 

Ki lometer per second 

Rate of Displacement Gain Ratio, per Second 

Kennedy Space Center 

Ki lowatts 



e 

A 

^' 

(J 

4* 

LAN. SW. 
L/B 



lb., 
LBp 

LBm 
L/D 

LDR 

Lf. 



LB 



Pitch Angle 
Delta Difference 
Yaw Angle 
Rol 1 Angle 

Mean Value (degrees) 
Standard Deviation Angle 
Pitch Rate (deg./sec.) 
Pitch Tip-off (deg./sec.) 

Yaw Rate (deg./sec.) 
Yaw Tip- Off (deg./sec.) 

Lanyard Switch 
Lower B-Section 
Pound 

Pounds Force 
Pounds Mass 
Lower D-Section 
Leader 
Life 



XXV 



SYMBOLS AND ABBREVIATIONS Continued 



Lmt. 

LOS 

L.O.WT 

LRC, LaRC 

LT 

LTRS 

LTV 

LV COORD. 

LMSC 

LWP 

Lwr . 



Limi tt ing 

Loss of Signal 

Lift-Off Weight 

Langley Research Center 

Left 

Letters 

Ling Temco Vought (Later Changed to LTV INC, 

Launch Vehicle Coordinator 

Loockheed Missiles and Space Company 

Langley Working Paper 

Lower 



M 

M. 

M. 

M 

M 

M-2 

M-H 

MAB 

MAGSAT 

MARK 

MAT'L 

max. 

Maint 

MCR 

MDC 

Mech. 

Mech. 

MER 

MFC 

MGSE 

MIG 

Misc. 

MO. 

M, MOD, MODS 

MOPS 

MOS. 

MPS 

MRA 

MRB 

MSD-T 

MSO 

Mfg. 

MSS 

MTRS 

MTS 

MWG 

MOD 



Scout Configuration as X-2M or X-3M 

Meters 

Master (Lead Man) 

Pitch Moment: Disturbance 

One Mi 1 1 ion 

Air Force Fourth Stage 

Minneapolis Honeywell 

Missile Assembly Building 

Magnetic Particle Satellite 

Scout Launcher 

Material 

Maximum 

Maintenance 

Motorola C-Band Beacon 

Mission Director Center 

Mechanical Engineer 

Mechanism 

Mechanical Equipment Room 

Mechanical Fit Check 

Mechanical Ground Support Equipment 

Miniature Integrating Gyro 

Mi seel laneous 

Monthly 

Modification to Contract 

Missile Operations Phone System 

Months 

Radar System 

Material Review Action 

Material Review Board 

Missiles and Space Division, Texas 

Mission Support Office, WTR 

Manufacturing 

Missile Space System 

Motors 

Meteroid Technological Satellite 

Mission Working Group 

Ministry of Defense 



XXVI 



SYMBOLS AND ABBREVIATIONS Continued 



N 

N 

NA 

NACA 

NAD 

NORAD 

NAS 

NASA 

NAVPLANTREPO 

NAVPRO 

NAVASTROGRU 

NDT 

N.D.T.T. 

NEMAR 



Navy 

Yaw Moment -FT/LBS 

Navy 

National Advisory Committee for Aeronautics 

Navy Ammunition Depot 

North American Air Defense 

NASA Contract Designation 

National Aeronautics And Space Administration 

Naval Plant Representative Office 

Naval Plant Representative Office 

Navy Astronautics Group 

Nondestructive Test 

Nondestructive Test Techniques 

Near Earth Mission Analysis Routine 



N.M. 



NH 
N. Ml 

Nz 
N.O. 

NOCC COORD 

NOVA 

NOTS 

NPE 

NRL 

N/TM 

NTR 



OA 

OAB 

OAST 

OART 

OD, O.D. 

OFO 

OLC 

Ops. 

OSB 

OSCAR 

OPS DIR 

OSF 

OSS A 

OST 

OV 

P 
P 

PA 
PAET 



Communication Frequency at San Marco 

Nautical Miles 

Nitrogen 

Number 

Network Operations Control Center Coordinator 

Navigation Satellite 

Navy Fifth-Stage Motor 

Neutral Point Explorer 

Naval Research Laboratory 
NAASA Telemetry Station 
NASA Test Representative 

Orbit 

Office of Applications 

Ordinance Assembly Building 

Office of Aeronautics and Space Technology 

Office of Aeronautics and Research 

Outside Diameter 

Orbiting Frog Otil ith 

Operations Logistics Coordinator 

Operations 

Operational Support Building 

Navy Transit Satellite 

Operations Director 

Office of Space Flight 

Office of Space Science and Applications 

Office of Space Transportation 

Designation for Air Force Vehicle 

Probe 

Process ing 

Physics and Astronomy 

Planetary Atmospheric Experiment Test 



XXVI I 



PBAA 

PBAN 

PCM 

PD 

PAM/FM/FM 

PDT 

pers., prsnl 



Pkg. 

P/L 

PLOO 

PMEL 

PMR 

PP 

PQ 

Pred. 
PREP. 
Pres. 
Prgm. , 



Prog, 
PROJ. COORD, 
PR OB. 
psi 
pt. 
PST 
PU 

P21A 
P76 



SYMBOLS AND ABBREVIATIONS Continued 

Polybutadiene Acrylic Acid 

Polybutadiene Acrylic Acr i lonitr i le 

Pulse Code Modulation 

P i tell Down 

Pulse Amplitude Modulation Frequency Modulation 

Pacific Daylight Time 

Personnel 

Package 

Pay load 

Pacific Launch Operations Office 

Plant Maintenance Electrical Laboratory 

Pacific Missile Range 

QCEB-PP-011, Quality Control Document 

Propulsion Qualification Test 

Pred icted 

Preparation 

Pressure 

Program 

Project Coordinator 

Probabil ity 

Pounds Per Square inch 

Point 

Pacific Standard Time 

Pitch Up 

NASA Probe 

Air Force Satellite 



q 

Q.A. 
Q.C. 
QCEB 
QCPP 
QRRR 
QUAL 

R 

R 

RAM 

Reconf ig, 

Recert 

RCO 

RCS 

RSD 

R-Day 

R 

REF 

REC 

Red. 



Pressure 

Q,ual ity Assurance 

Qual ity Control 

Quality Control Evaluation Board 

Quality Control Program Plan 

Quarterly Replenishment Requirements Report 

Qual if ication 

Rev is ion 
Recertify 

Radio Attenuation Measurement (LaRC Spacecraft) 

Reconfigure or Reconfiguration 

Recertif icat ion 

Range Control Officer 

Reaction Control System 

Research and Development 

Reconstruction Day 

Task R (for Special Requirements) 

Reference 

Receiving 

Redes ign 



XXVI I 



SYMBOLS AND ABBREVIATIONS Continued 



REL 

REMO 

REPS 

REQ'D 

Ews .Reps, 

Res. 

Re 

RETRO 

Rev. 

Rev. 

Retrans . 

R/F 

RFD 

RFI 

RF, R/F 

RMRB 

RKT 

R-O-Day 

RAE 

RPL 

RMS 

RPM 

RPM 

RPT 

RR 

R/S 

RT 

RTG 

RV 

R/Y 



Release 

Resident Engineering and Management Office 

Representatives 

Requi red 

Resident Representatives 

Resistance 

Reentry 

Retrograde 

Rev is ion 

Review 

Retransfer 

Radar Frequency 

Sandia Corporat ion-AEC Spacecraft 

Radio Frequency Interference 

Radio FrequencyRMRB 

Rocket Motor Review Board 

Rocket 

Zero Ready Day 

Royal Aircraft Establishment 

Redstone Propulsion Laboratory 

Root Mean Square 

Revolutions per Minute 

Program Management Funds 

Report 

Certified Twice 

Remove From Storage 

Right 

Radioisotope Thermal Generator 

Vehicle Rel iabi 1 ity 

Roll-Yaw 



S 

S 

SA, S.A. 

SAGE 

SAI 

SAMSO 

SAMTEC 

SAS 

SB 

S-Band 

SBASI 

SCAMA 

Sched. 

SCOUT 

Scout Coord. 

S/C MON 

S/C TC 



Scout 

Success 

Subauthor izat ion 

Stratopheric Aerosol and Gas Experiment 

Science Applications, Inc. 

Space and Missile Systems Organization 

Space and Missiles Test Center 

Small Astronomy Satellite 

Scout Boosted Systems Division 

Radar Frequency Band 

Single Bridgewire Apollo Standard Initiator 

Switching Conferencing and Monitoring Arrangement 

Schedule 

Space Orbiting Utility Test - NASA Launch Vehicle 

Scout Coordinator 

Spacecraft Monitor 

Spacecraft Test Conductor 



XXIX 



SYMBOLS AND ABBREVIATIONS Continued 



SEAM 

Sec. 

Sec. 

SECOR 

Sep. 

SEMTECH 

SERT 

SEV 

SFP 

Shlf. 

Sh. Lf. Ext, 

S/L 

SLC 

SLUG-FT^ 

SM 

S-M 

SN, S/N 

SNI 

SOLRAD 

S-O 

SOP 

SPAC 

SPEAR 

SPFLTR 

SPEC. 

SPO 

SRT 

SS 

s2bT 

S^T 

SSS-A 

SST 

ST 

ST 

Stand. STD 

Stdy 

STR 

STA 

STAT. 

STAR 

STADAN 

STDN 

STG. 

STO 

STRAD 

SUI 

Sub. 

Subs. 

Sup. 



Systems Engineering and Maintenance 

Section 

Seconds 

Army Satel 1 ite 

Separation 

Electronic Diode (T.I.) 

Lewis Laboratory Spacecraft 

Systems Evaluation Vehicle 

Single Failure Point 

Shelf 

Shelf Life Extension 

Shelf Life 

Standard Launch Complex 

Units of Measurement for Inertia 

San Marco 

Sustaining - Major Contracts 

Serial Number 

Ground Station 

Solar Radiation Satellite 

Sustaining Obligations - Others 

Standard Operating Procedures 

Scout Program Account ing Control System 

Scout Performance Evaluation and Ascent Reconstruction 

SPEAR Filter Computer Control System 

Specif icat ions 

Scout Project Office 

Scientific Research & Technology 

Space Science 

Scout Standard Environmental Test 

Scout Standard Systems Test 

Small Scientific Satellite-A 

Supersonic Transport 

Scout Test 

Development Vehicles 

Standard 

Study 

Structural 

Station 

Static 

Government Requirement that Rocket Motors Carry the Name of a Star 

Space Tracking Data Acquisition Network 

Space Tracking and Data Acquisition Network 

Stage 

Space Transportation Office 

Air Force Organization 
Injun/Air Density Experiment 
Subsequent 
Subcontractors 
Support 



XXX 



SYMBOLS AND ABBREVIATIONS Continued 



Sust. 

SVAFB 

S/W 

SW 

SYS 

T 

T.C. 

TCC 

T/D 

TDI 

Tech. 

TEM 

TIP 

Tip-off 

TIR 

TM, T/M 

TMC 

T.O. 

TOLIP 

TPGEN 

TRANSAT 

■ms 

Tst. 

Tsts. 

TTY 

TUB. 

TX 

U/B 

U/D 

UHF 

Ult. 

UK 

UN I VAC 

Upr. 

USAF 

UT 

UTC 

VC 

VAFB 

VOL 

VEGA 

Veh. 

Veh., VEH 

VHF 

VMSC 

Vol. 



Sustaining 
Beacon Radar 
Stop Work 
Switch 
Systems 

Time 

Thiokol Chemical 

Thiokol Chemical Company 

Tear Down 
Tele-Dynamics, Inc. 

Technician 

Thiokol/Elkton Motor 

Transit Improvement Program 

Tip-off Angle 

Test and Inspection Report 

Telemeter, Technical Memorandum 

Communications Circuit at San Marco 

Task Order 

Trajectory Optimization and Linearized Pitch Computer Program 

Tape Processor and Generator 

Navy Satel 1 ite 

Primary Source of T/M Data 

Testing 

Tests 

Teletype 

Tubing 

Prefix to Motor Number 

Upper B Section 

Upper D Section 

Ultra High Frequency 

Ultimate 

United Kingdom 

Type of Computer in the LMSC Central Computing Facility 

Upper 

United States Air Force 

United Technology 

United Technology Corporation 

Vought Corporation 

Vandenberg Air Force Base 

Voice Direct Line 

Beacon 

Vehicle Engineer 

Vehicle 

Very High Frequency 

Vought Missiles and Space Corporation 

Volume 



XXXI 



SYMBOLS AND ABBREVIATIONS Concluded 



VWZC 
VSD 

WA 

WFC 

Wl 

WLOD 

WTR 

WMV 



6595th Space Test Group, AFV/TR 
Vought Space Division 

Work Authorization 

Wallops Flight Center 

Wallops Island 

Telemetry Station (Western Launch Operations Doppler Directorate) 

Western Test Range 



X 
X 
X 
XLDB 



Experiment 

Experimental 

Sh ipping 

Type High Energy Propel lant 



XSR 



Fourth Stage Motor 



YL 
YR 



Yaw- Left 
Yaw-Right 



XXXI I 



OF pocn QUAirry 



SCOUT PROGRAM FISCAL YEAR FUND EXPENDITURES CODE 



NASA 



INTERNATIONAL 



AIR FORCE 



NAVY AEC YEAR 



DEV. & SRT SEAM PROD. AEROS ESRO 



VA 
VB 
VC 
OD 
OE 
OF 
OG 
OH 
0! 
OJ 



SD 
SE 
SF 
SG 
SH 



PA 
PB 
PC 
PF 
PE 
PF 
PG 
PH 
PI 
PJ 
PK 
PL 
PM 
PX 
PW 
PQ 
PZ 
PT 
PV 
PS 
PU 
PO 



AX 
AW 
AQ 

AT 
AV 



ITALY 



UK-Xif 59-6 
UK-5 62-6 68-F 

UK-6 63-32 63-29 66-95 0071 



EJ 






EK 






EL 




UL 


EM 




UM 
UX 


EW 




UW 


EA 




Ud 
UZ 




IT 


UT 




IV 


UV 




IS 


US 




lU 


UU 




10 


UO 




IP 


CODE 



RA 








NA 


60-61 


RB 


YB 






NB 


62 


RC 


YC 






TC 63 


RD 


YD 








6lt 


RE 


YE 






NW 


65 


RF 


YF 








66 


RG 




NG 






67 






NH 


YH 




68 


Rl 


Yl 


NJ 






69 
70 






NK 




NK 


71 






NL 


YL 




72 






NM 






73 






NX 


YX 




Ih 








YW 


NW 


75 








Yd 




76 








YZ 




7T 








YT 


NT 


77 








YV 




78 








YS 




79 








YU 


NU 


80 








YO 




81 








YP 




82 



A - AEROS-B 

E - ESRO 

I - ITALY 

N - NAVY (DIRECT 6 A.F. (66-95)) 

- NASA-SS-SRT (l80) 

P - NASA PRODUCTION {k3Q) 

R - AIR FORCE 

S - NASA SYS. ENGR. S MAINT. (^(97-90) 

T - AEC 

U - UK-X^i, UK-5, UK-6 

V - NASA DEVELOPMENT FUND (89O) 

Y - NAVY BY AIR FORCE (63-29) AND (68-F-0071) 



A 1961 


X 197'* 


B 1962 


w 1975 


c 1963 


Q 1976 


D 196'* 


z 1977 


E 1965 


T 1977 


F 1966 


V 1978 


G 1967 


s 1979 


H 1968 


u 1980 


1 1969 


1981 


J 1970 


P 1982 


K 1971 




L 1972 




M 1973 





XXXI I I 



INTRODUCTION 



NASA's unmanned launch vehicle program consists of various liquid and solid 
fuel motor stages that propel a spacecraft into space. The smallest unmanned 
launch vehicle, with orbital capability, is the Scout. The Scout is distin- 
guished by being the only all-solid fuel major NASA launch vehicle. 

The Scout program, managed by the NASA Lang ley Scout Project Office, has been 
divided into eight phases. The data of phases one through five have been 
published by NASA in I969 and 1974. 

This publication is dedicated to Phase VI and includes updated information on 
Phases I through V and advanced planning information on Phase VII. 

The Scout dates back to the beginning of the United States' space program. 
Its conception was at the NACA Langley Research Center. For many years the 
NACA Pi lot less Aircraft Research Division had been conducting research programs 
investigating supersonic and hypersonic flight programs from Wallops Island, 
Virginia. In 1957 a group of engineers, using the historical data from the 
launching of many mult i-sol id-propel lant rocket combinations, started an 
investigation of various combinations of existing solid propel lant motors that 
could orbit a small satellite. This investigation resulted in Scout configu- 
ration X-1 after many motor combinations were proposed. 0' 

The first contract was awarded in May of 1958 for the second stage. Many 
contracts have been awarded since then, including the major contracts to the 
Vought Corporation, who later became the Scout prime contractor as a result 
of winning the initial competition in April 1959. The first vehicle (ST-1), 
manufactured by Chance Vought Aircraft Company and assembled by the Langley 
Research Center, was launched on July 1, I96O. The first Phase VI vehicle 
was launched August 16, I97I . 

The Scout Project Approval Document states the following objectives: (a) to 
procure Scout launch vehicles, including launch services, for the accomplish- 
ment of NASA missions in Space Science, Applications and in Space Technology; 
in addition, to procure Scout launch vehicles and services on a reimbursable 
basis for other authorized users; (b) to provide engineering services for 
production vehicles, for corrective changes or improvements in systems and 
procedures as required to maintain the operational capabilities of the Scout 
launch vehicle system; and (c) to provide for major product and performance 
improvements as may be required and approved in support of Scout's role in 
the national launch vehicle family. 

The Scout Project Development Plan states the following objectives: 

(a) Development. To develop a relatively inexpensive, reliable, 

sol id-propel lant rocket vehicle for use as a satellite launcher and research 
vehicle. 

(b) Operational. To maintain a standard configuration vehicle suitable 
to the requirements of NASA and the Department of Defense. Similar launch 

'■'Configurations are described in table I. 



XXXIV 



equipment, checkout equipment, and procedures compatible with the vehicle 
shall be maintained and repaired or replaced as required at Wallops Island, 
Virginia, and Vandenberg Air Force Base, Western Test Range, California. To 
improve production vehicles, specifically by the correction of deficiencies 
uncovered during operational use of the vehicles. 

(c) Reliability. To achieve and maintain a success ratio of 90 percent 
or greater. 

(d) Launch. To coordinate and launch approved missions for various 
payload agencies. 

(e) Major Product Improvement. Product improvement of the Scout vehicle 
has been primarily aimed at increasing the overall vehicle reliability, and 

at improving vehicle performance by incorporating selective changes compatible 
with the basic Scout design. Performance improvements have been achieved by 
incorporating improved motors for all four stages of the Scout, with a performance 
gain at the start of Phase VI of approximately 220 percent, and 320 percent at the 
conclusion of Phase VI. 

In addition to the wide variety of NASA research programs that have been conducted 
in space and in reentry technology, there have been other significant programs 
and users. The Department of Defense has had a significant program in space 
research. The U.S. Navy Strategic Systems Projects Office has been a major 
continuing Scout user for the Transit navigation satellite program. The Transit 
spacecraft provides navigation data not only for the operational fleet but for 
commercial shipping worldwide. Cooperative and reimbursable spacecraft launches 
have been conducted for France, Germany, Italy, the Netherlands, the United 
Kingdom and the European Space Research Organization making Scout a truly inter- 
national program. 

A significant addition to the Scout capability was realized with the establish- 
ment of the Scout San Marco launch complex near the equator off the coast of 
Kenya. The Italian Centre Ricerche Aerospaziali had the bold concept of placing 
Scout launch and range facilities on two mobile platforms off the Kenya coast in 
Ngwana Bay. On April 26, 196?, with the successful launch of the Italian's 
atmospheric physics spacecraft, San Marco B, the soundness of this concept was 
demonstrated. A successful series of eight (the eighth was the first launch of 
Phase VII and the first F-1 configuration) launches has been conducted at this 
facility with Italian, United Kingdom, and U.S. spacecrafts. 

Seventy-four Scout space launches have preceded the first launch of Phase VI. 
By the time S-192 (the last and fifteenth launch of Phase VI) was launched on 
May 14, 1981, ten Scout vehicles of Phase VII had been launched. Phase VI costs 
actually ended on May 22, 1976, five years prior to the launch of the fifteenth 
and final Phase VI Scout. The fourteenth (S-179) Phase VI Scout was launched 
on May 22, 1976. From 1976 to I98I vehicle S-192 was a stand-by vehicle for the 
Navy Transit Program. The Navy Transit Satellite Program was extremely success- 
ful causing a delay in replacement satellite requirements. 



XXXV 



Figure 1 outlines the Scout program schedule of launches by year, including 
vehicle and satellite designations. Figure i also shows the launch frequency 
per year and the phase designations. Note that Phase VI slow launch schedule 
covered a six-year span for the fourteen vehicles. Phase VII has already 
expanded its launch schedule of the sixteen vehicles beyond an eight-year span. 
Phase VI was accomplished at a 100 percent success launch record. This great 
accomplishment resulted in a 95 percent overall production vehicle success 
rat io. 

The historical data (technical and financial) of the Scout program has been 
documented since its inception and takes pride in its technical success and 
its financial achievement. It is the intention of the author to present the 
history of all technical systems and administration of the Scout Program during 
this phase. 



SPECIAL RECOGNITION 



Special recognition is given to the support of the Scout Project Office for 
their effort on behalf of this publication, especially to Nell Turpen and 
Elaine Crawford for their excellent support. 















































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CHAPTER I - SCOUT LAUNCH VEHICLE PROGRAM 



ORIGINAL FAQS jb 
OF POOR QUALITY 



The Scout launch vehicle program is divided into eight phases described as 
fol lows: 



(1) 


Phase 


1 


(1) 


Phase 


II 


(1) 


Phase 


III 


(2) 


Phase 


IV 


(2) 


Phase 


V 


(3) 


Phase 


VI 




Phase 


Vil 




Phase 


VIM 



Development of the Scout Launch Vehicle (9 vehicles) 
Prototype of Production Scouts (14 vehicles) 
Scout Recertif icat ion Program {^k vehicles) 
Systems Management of Scout (25 vehicles) 
Incentive Procurement (15 vehicles) 
Award Fee Procurement (15 vehicles) (4) 
Continuing Program (15 vehicles) (4) 
Final Scout Program - D.O.D. (10 vehicles) 



This document includes all aspects 
of Phase VI and is the final report 
on this phase. The time period if 
April 1968 through June 30, 1976. 
The first Phase VI launch was Scout 
vehicle S-I8OC, configuration B-1 , 
placing spacecraft CAS-A into an earth 
orbit (figure 2). The designation for all 
Scout configurations is listed in Table I. 
Figure 3 details the Scout orbit capabil- 
ities and also shows configuration details. 

The Scout launch vehicle is a four- 
stage guided research booster utiliz- 
ing solid propellent rocket motors 
capable of boosting payloads of varying 
sizes in orbital, reentry, and probe 
missions. Figure k shows a sketch of 
a typical Scout vehicle. Figure 5 
illustrates the motor systems and parts 
of Scout-D. Only one Scout-D was previously 
launched in Phase V. Eight of the 
Phase VI vehicles were Scout-D. Scout 
vehicle I9IC had a BE-3 fifth stage. 
This was the only 5-stage Scout 
vehicle. Five previous Scout vehicles 
have had a NOTS-17 pay load kick-stage 
not part of the booster. Figure 6 
shows the launch of S-I9IC. This 
vehicle contained many new program 
developments. Scout I9IC was equipped 
with the first high pressure third 



N 




SjSur" 



Figure 2,- Scout vehicle S-I80. 



(1) All aspects of Phases I, 11, and II are covered in a final report 
published in Langley Working Paper 804 dated 11/20/69- 

(2) All aspects of Phases IV and V are covered in a final report published 
in Langley Technical Memorandum TM X- 72628. 

(3) Detailed in this publication. 

{k) The launch of the 15th vehicle of Phase VI was part of the Phase VII 
program. 



stage (Antares I IB), and the first Scout fifth-stage attitude correction 
system as well as the above-mentioned first fifth-stage BE-3 motor. 





TABLE 1. 


DESIGNATION 


OF SCOUT 


CONFIGURATIONS 








FIRST 


SECOND 




THIRD 




FOURTH 




FIFTH 


QUANT IT Y''< 


CONFIGURATION 


STAGE 


STAGE 




STAGE 




STAGE 




STAGE 


LAUNCHED 


X 


Algo 


1 lA 


Dummy 




Antares 


A 


None 




None 


1 


X-1 


Algo 


1 lA 


Castor 


A 


Antares 


A 


Altair 


lA 


None 


7 


X-IA 


Algo 


i lA 


Castor 


A 


Antares 


A 


Altair 


lA 


NOTS-17 


1 


X-2 


Algo 


lA 


Castor 


A 


Antares 


lA 


Altair 


lA 


None 


2 


X-2B 


Algo 


lA 


Castor 


A 


Antares 


lA 


Altair 


MA 


None 


1 


X-2M 


Algo 


lA 


Castor 


A 


Antares 


lA 


M-2 




None 


3 


X-3 


Algo 


MA 


Castor 


A 


Antares 


lA 


Altair 


lA 


None 


6 


X-3A 


Algo 


MA 


Castor 


A 


Antares 


lA 


Altair 


lA 


NOTS-17 


2 


X-3C 


Algo 


MA 


Castor 


A 


Antares 


lA 


None 




None 


1 


X-3M 


Algo 


MA 


Castor 


A 


Antares 


lA 


M-2 




None 


1 


X-4 


Algo 


MA 


Castor 


A 


Antares 


lA 


Altair 


MA 


None 


13 


X-4A 


Algo 


MA 


Castor 


A 


Antares 


lA 


Altair 


MA 


NOTS-17 


2 


X-5C 


Algo 


MA 


Castor 


lA 


Antares 


lA 


None 




None 


1 


A 


Algo 


MB 


Castor 


lA 


Antares 


lA 


Altair 


MA 


None 


11 


A-1 


Algo 


lie 


Castor 


lA 


Antares 


lA 


Altair 


MA 


None 


1 


A-2 


Algo 


lie 


Castor 


lA 


Antares 


IB 


Altair 


MA 


None 





8 


Algo 


MB 


Castor 


lA 


Antares 


lA 


Altair 


MIA 


None 


25 


B-1 


Algo 


lie 


Castor 


lA 


Antares 


lA 


Altair 


IMA 


None 


5 


B-2 


Algo 


lie 


Castor 


lA 


Antares 


IB 


Altair 


IMA 


None 





*c 


Algo 


lie 


Castor 


lA 


Antares 


lA 


Altair 


IMA 


BE-3 





D-1 


Algo 


IMA 


Castor 


lA 


Antares 


lA 


Altair 


MIA 


None 


15 


E-1 


Algo 


IMA 


Castor 


lA 


Antares 


IB 


Altair 


MIA 


BE-3 


1 


F-1 


Algo 


IMA 


Castor 


lA 


Antares 


IB 


Altair 


MIA 


None 


2 


G-1 


Algo 


IMA 


Castor 


lA 


Antares 


MA 


Altair 


IMA 


None 


2 


OTHER REFERENCE 


DESK 


5 NAT IONS 


: 

















Algol l-Aerojet Senior, 
Algol I l-45KS-100,000 
Algol II lA • 



33KS-12O,O0O 



Castor I-XM33E5, XM-75, 27KS-55,0O0 
Castor I IA-TX35^-3 • 

Antares l-X-254, XM-70, 38DS-1it,000 

Antares I lA, X-259, 33DS-21 ,5^0 

Antares I IB •, HP-X259-Bif 

Antares IMA, Thiokol 



Altair I-X248, XM-69, 40DS-3100 
Altair II-X258, XH-Sk, 2^^05-5850 

• Altair IMA, FW4S or XSR 57-UT-1 
TEM640-1, 27.4KS6,016, STAR-20 

NOTS-17, XM-78, N0TS100-17, 43K-882 

• BE-3A9/15-DS-5770 (Bacchus engine, 

Thiokol motor) 



"Program canceled. 

""Includes data through S-203C (S-199 on standby) 

•Only motors in inventory. 



OF POOR QUALITY 



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ORIGINAL PAGE h3 
OF POOR QUALITY 




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^ !! 




Fiqure 6.- S-19IC Launch Vehicle. 



This additional stage helped the Scout I9IC satellite obtain an apogee of 
102,015.25 km with a polar orbital period of 3032.4 minutes. Prior to Scout 
191c the maximum apogee was the satellite of Scout 163C at 26,912.3 km with 
an equatorial orbital period of 469 minutes. 

All of the fifteen Scouts in Phase Vl were successful orbital missions. The 
last reentry mission was Scout vehicle I7IC, a Phase V vehicle, launched 
September 30, 1970. Only one additional probe mission was scheduled, Scout 
vehicle 193C, a Phase VII vehicle. Information on Scout probe and reentry 
missions are documented in Appendix A. However, for all trajectories, the first- 
stage motor remains attached to the vehicle after burnout and the vehicle 
coasts to an altitude that results in a nominal q of approximately kO pounds 
per square foot at first-stage separation. The maximum q is 2,200 pounds 
per square foot which occurs during first-stage burning and is reached at about 
36,000 feet altitude. The majority of Scout launch requirements have been 
aimed at achieving near-earth orbits. Figure 7 illustrates a profile in a 
typical Scout mission. Because of the strong emphasis in the past and in the 
foreseeable future on orbit missions, the bulk of the performance data presented 
will deal with this aspect of Scout orbital capability. 

For orbit missions the Scout vehicle utilizes the first three stages to boost 
the fourth stage plus payload to the desired injection altitude. The fourth 
stage is then used as the injection stage by accelerating the payload to the 
desired orbital velocity. The injection altitude is controlled by a predeter- 
mined pitch-rate program which commands the guidance and control system to 
steer the vehicle along the desired trajectory. Figure 8 illustrates the Scout 
boost trajectory pitch program orbit mission. Orbit inclination is determined 
by the latitude and vehicle heading angle at injection. These parameters are 
controlled, for a given mission, by the launch azimuth and any heading angle 
change obtained by yaw torquing. 

Figure 9 illustrates a typical Scout orbital mission boost trajectory. The 
second stage is not ignited until the dynamic pressure reduces to the level 
which insures second-stage control system capture. A short coast phase 
following first-stage burnout is sometimes necessary to obtain the proper con- 
ditions for second-stage ignition. When the second stage is ignited, simulta- 
neous separation from the first stage occurs. 

A nominal coast period of 5 seconds follows second-stage burnout during which 
the payload heat shield is ejected. Third-stage Ignition and second-stage 
separation then occur simultaneously. During the first three boost phases the 
vehicle pitch-rate program is designed to command the vehicle to fly a zero- 
lift (gravity turn) trajectory. Following third-stage burnout the control 
system orients the vehicle to the proper injection attitude. Following a long 
third-stage coast phase (200 to 6OO seconds, depending upon the mission) the 
payload plus fourth stage is then ignited and accomplishes the necessary injec- 
tion into orbit. The payload may or may not be separated from the empty fourth 
stage following burnout. Table II lists the sequence of events of a typical 
launch. 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPK 




F I gyre ^. - Typical boost ascent and pay load injection into orbit. 



10 



BOOST TRAJECTORY PITCH PROGRAM 

ORBIT MISSION 




TIME - SEC. 

Figure g.- Scout boost trajectory pitch program orbit missic 



BOOST TRAJECTORY 
ORBIT MISSION 



OF POOR QUAL:r. 



COAST 



THIRD 
STAGE 






COAST 

SECOND 
STAGE 



I COAST 



FIRST 
STAGE 



SPIN 

UP INJECTION 

,_▼ r 

FOURTH 
STAGE 



ORBIT 



Figure 9.- Typical Scout orbital mission boost t 



rajectory. 



m 



ORIGINAL FAC 

OF POOR QUALITY 



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12 



Figures 10, 11, 12, 13, and \k illustrate the circular orbit performance of 
the Scout launch vehicle. 



The data illustrated in figures 10, 11, and 12 are for Scout D. 
sisted of five configurations designated as follows: 



SCOUT 



CONFIGURATION 



SCOUT 



CONFIGURATION 



SCOUT 



Phase V I con- 



CONFIGURATION 



178c 


A-l 


183C 


179C 


B-1 


184c 


180C 


B-1 


185C 


181C 


D-1 


186C 


182C 


B-1 


187C 



B-1 


188C 


D-1 


D-1 


189C 


D-1 


D-1 


190C 


D-1 


D-1 


191C 


E-1 


B-1 


192C 


G-1 



B-conf igurat ion orbital parameters were presented In a previous publ icat ion V ' ) . 
The final B-1 Scout was the ninety-fourth Scout launch on May 22, 1976 desig- 
nated Scout vehicle 179CR. The one and only Scout A-1 configuration was the 
Scout 178c vehicle launched on October 29, 1973- This was the eighty-fourth 
Scout launch. Figure 3 includes configuration A-1 data. Detailed information on 
has not been presented because configuration A-1 was never used again. Configu- 
ration E-1 is a Scout-D with a fifth stage. Figure 14 presents the orbital 
capabilities of a five-stage Scout launched from VAFB. Scout vehicle S-192C 
was the fifteenth and last vehicle of Phase Vl configured as G-1. 

Performance capability available for the users in the time period of 1971-1974 
was increased upon the completion of the Algol III development program. The 
Algol III replaced the Algol MB as the first-stage motor. The new motor which 
has 1.83 X 10° pounds- seconds total impulse more than the Algol II is also five 
inches larger in diameter (45 inches). This increase in diameter provides 
6,800 pounds of additional propel lant and also incorporates improved materials 
and techniques. The increase from Scout B-1 to Scout D-1 can be noted in 
figure 3. The first Scout D-1 was Scout S-184 from Wallops Island shown in 
figure 15- 

Scout vehicles are launched from three geographical areas as shown in figure I6. 
The easterly launch site is Wallops Island as mapped in figure 17(a). The 
Vandenberg Air Force Base site as shown in figure 17(b) is for polar orbits. 
Figure 17(c) shows the African launch site (Italian government-owned) which is 
used for equatorial orbits. Figure 18 shows S-190 being prepared for launch 
at the San Marco Range. The Italian engineers for the San Marco-B spacecraft 
are checking the spacecraft before launching. The spacecraft was launched 
from a platform at sea off the coast of Kenya, Africa, at 10:05 G.M.T., 
February 18, 1974. Tracking data from NASA's Space Tracking Data Acquisition 
(STADAN) stations in Quito, Equador, and Lima Peru, indicate that the spacecraft 



A-1 



(l)Published in Lang ley Technical Memorandum TMX- 72628, 



13 



OF POOR QUkU 






NCE 


WALLOPS ISLAND LAUNCH - DUE EAST 
VAFB LAUNCH - POLAR ORBIT 
SAN MARCO LAUNCH - DUE EAST 








-WALLOPS 
LAUNCH 

(37.70 INCLINATION) 

t 






RBIT PERFORMA 








// 


1 




-SAN MARCO 
LAUNCH 

<2.930 INCLINATION) 

1 






11 


1 








/ 






\ 


V/ 




N 




O 




/ 


7 




VAFB 1 

LAUNCH 

(90° INCLINATION) - 




CIRCULA 




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ORBIT MISSION 
PERFORMANCE 

WALLOPS ISLAND 
LAUNCH 

DUE EAST 



14 



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OUSIIS — 


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100 200 )00 too 

ntiaa wiicht -poums 



Figure 11.- Scout-D easterly orbit capability. 



ORBIT MISSION 
PERFORMANCE 

VAFB LAUNCH 
POLAR ORBITS 



70000 
20000 




i 




















\1 


s, 
















z' 4000 

LJ 

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100 
















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PAYLOAO UEIGNT-POUNOS 



soo 



Figure 12.- Scout-D polar orbit capability. 



15 



ALGOL IMA 

CASTOR MA 

ANTARESIIB 

ALTAIR MIA 

1.07 METER DIA. HEATSHIELD 



OF POOR QUAliTY 
SCOUT F 1 



ORBIT INCLINATION = 2.9° 



I 

m 
Q 

D 



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O 
O 
a. 

< 



100000 r 

80000 



60000 



40000 



30000 




50 



100 150 

PAYLOAD WEIGHT - KG 



200 



250 



Figure 13.- Elliptical Orbit Performance - Equatorial San Marco Launch. 



OF POOR QUALiTY 



ALGOL MIA 
CASTOR II A 
ANTARES MB 
ALTAI R III A 
ALCYONE lA 



200000 



16 
SCOUT E-1 

ORBIT INCLINATION = 90° 



m 
O 

13 



O 

Q. 
< 




6000 



4000 






2000 



1000 




20 40 60 

PAYLOAD WEIGHT - KG 



80 



Figure 14.- Apogee altitude - Vandenberg AFB Launcii. 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPFT 



17 



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Figure 15.- Scout S-}84, First 0-1 using the first Algol i! lA. 



18 



OF POOR QUALITY 



1 I I I I aSiYTl 







J I L 



J L 



(Detailed San Marco Program 
is covered in appendix A.) 



J I I ' I I I I L 



Figure 16.- Total Scout geographical complex. 



is in tine prescribed equatorial orbit witli an apogee and perigee close to 
nominal. The satellite, first ever to be launcined from a platform at sea, was 
designed to obtain continuous equatorial air density measurements. The Italian 
Commission for Space Research (CRA) designed and built the 368-pound spacecraft, 
The entire launch complex was also a responsibility of the CRA. The project 
was carried out under a cooperative international agreement between the 
Italian Commission for Space Research and the National Aeronautics and Space 
Administration. Figures 19 and 20 show the base camp and blockhouse of the 
San Marco complex. 



The Mark I launcher was used for the initial Scout launches but has been 
replaced by Mark II. Scout S-12^was the first Scout vehicle using the Mark II 
launcher which was launched July 20, 1964. The Mark II launcher (figures 21 
and 22) is provided with a movable base to permit azimuth control between 
65 degrees and 205 degrees and a canti levered elevating launch boom to permit 
pitch control to the 90-degree position required for launch. The launcher with 
the Scout vehicle in position permits check out of the vehicle in the horizontal 
pos i t ion . 



o 

LU 
OQ 



Q 

> 




ORIGlPiAL PASS 13 
OF POOR QUALITY 



2 = 



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< 

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1 


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20 ORIGINAL PAGE 

BLACK AND WHITE PHOTOGRAPH 




c 



c 



c 

Q. 

Cj! 






BASE CAMP 



OF POOR QUALITY 




Figure 19-- San Marco Base Camp 



SANTA RITA 

PLATFORM 

BLOCKHOUSE 



■ RADIO ANTENNA 



- WIND TOWER 



HELIPORT 



KITCHEN, CAFETERIA 



QUARTERS. FIRST AID, 
RADIO 



CONTROL CENTERS 
AND VANS 



RANGE CONTROL, 
COMMUNILATIOriS 






T/M TRACKING 
ANTENNA 



S BAND RADAR VANS 
OmCAL TRACKER 




Figure 20.- Equatorial launch complex showing platform blockhouse. 



13 



np POOR QUAUTY 



OF POOR 



22 



^:^:x• - v— ncTi <n^ 



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a. 



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3 



(0 



3 



ORIGINAL PAGE IS 
OF POOR QliAi-iTY 



23 




1. DISPLAY CONSOLE (REF. ONLY) 8. 

2. ALTAIR RESTRAINT RING 9. 

3. FOURTH STAGE CRADLE 

4. ANTARES RESTRAINT RINGS 10. 

5. CASTOR RESTRAINT RINGS H. 

6. ALGOL FWD RESTRAINT RINGS 12. 

7. ALGOL AFT RESTRAINT RING 13. 



WORK PLATFORM 

SHORING JACK ASSEMBLY 10 REQ. 

(5 PLACES EACH SIDEl 

SECOND STAGE CRADLE 

THIRD STAGE CRADLE 

LANDING GEAR 

JOCKEY KINGPIN 




1. PITCH DRIVE ASSEMBLY 

2. LAUNCHER CONTROL PANEL . 
AFWTR ONLY (SEE SHEET 2) 

3. LUG ASSEMBLIES 

4. BEAM ASSEMBLY 

5. PAYLOAD FLYAWAY ARM 

6. D SECTION SUPPORT ARMS 
/. D SbL HON FLYAWAY AHM 
8. C SECTION UMBILICAL ARM 



9. C SECTION SUPPORT ARMS 

10. B SECTION UMBILICAL ARM 

11. LAUNCH ARMS 

12. SHIELD ASSEMBL\ 

13. BEARING ASSEMBLY 

14. AZIMUTH DRIVE ASSEMBLY 

15. LAUNCHFR CONTROL PANEL 
w.', OnLI see SmEET l! 

16. BASE STftUCTJPC 




PAYLOAD FLYAWAr ARM 

PAYLOAD COOLING 

D SECTION COOLING 

LAUNCH ARMS NITROGEN BOTTLE 

P'TCH SPEED COHTkOL 



LAUNCH ARMS 
a SECTION UMBILICAL ARM 
C SECTION SUPPORT ARMS 
C SECTION UMBILICAL ARM 
D SECTION FLYAWAY ARM 



11. D SECTION SUPPORT ARMS 



Figure 22.- Mark II Launcher and Transporter, continued 



24 



An electromechanical system is provided for erecting the vehicle to the 
vertical attitude. Erection acceleration is limited so that critical loads 
will not be imposed on the Scout vehicle and mission. 

Of the three Scout launch sites, Wallops Island represents a mean performance 
of the Scout capability of the two remaining Scout launch sites. Generally 
speaking, the Wallops facility has been used for circular and elliptical 
orbit work for inclinations 82 degrees to 22 degrees, reentry missions and 
probes. Polar orbit- are launched from Vandenberg Air Force Base, California, 
with an inclination range of ]kk degrees to 3^ degeees . San Marco launch plat- 
form, located off the east coast of Kenya, permits missions which require incli- 
nations from 79.5 degrees to 0.0 degree. 

The launch sites and inclination angles for the Phase VI Scout vehicles are as 
fol lows : 



Scout Vehicle 


Launch 


Site ^"^ 


Incl inat ion 


178c 


VAFB 


(43) 


90.20 


179CR 


VAFB 


(50) 


99.88 


180C 


Wl 


(34) 


50.16 


181C 


VAFB 


(42) 


97.20 


182C 


VAFB 


(40) 


90.13 


183C 


VAFB 


(39) 


83.00 


184c 


Wl 


(36) 


37.69 


185C 


VAFB 


(42) 


91 .10 


186c 


VAFB 


(46) 


97.20 


187C 


S.M. 


(7) 


2.86 


188c 


VAFB 


(44) 


98.40 


189C 


VAFB 


(47) 


98.04 


190C 


S.M. 


(6) 


2.90 


191C 


VAFB 


(45) 


89.78 


192C 


VAFB 


(55) 


90.15 



The San Marco facility is operated by the Centro Ricerche Aerospaziali of 
Italy. The capability of the Scout vehicle is enhanced by utilizing the San 
Marco facility due to its geographic location. San Marco performance data 
was presented in figures 10 and 13. 



(wphase VI did not include any probe or reentry missions. 
'^'Designates the number of the Scout launch from each site. 



25 



• 



CHAPTER II - SCOUT LAUNCH VEHICLE HARDWARE 



26 



With the heat shield in place, the Scout-D is typically some 76 feet in length 
with a launch weight of 48,600 pounds. Actual lift-off weights for Phase VI 
are listed below: (shown in pounds.) 



Vehicle No. 


L.O. WT.LBS 


Vehicle No. 


L.O. WT.LBS 


Vehicle No. 


L.O. WT.L 


178 


39,^99.14 


183 


39,721.60 


188 


47,580.73 


179 


39, 69'+. 34 


184 


47,732.22 


189 


47.534.45 


180 


39,726.46 


185 


47,514.10 


190 


47,724.91 


181 


47,408.69 


186 


47,684.23 


191 


47,671.81 


182 


39.701.55 


187 


39,936.89 


192 


47,777.99 



Vehicle S-191 was a five-stage configuration, Scout-E.^ All other Phase VI 
vehicles were four-stage configurations. Figure 23 is a sketch of the Scout 
vehicle showing primary dimensions. Figure 24 shows the inboard profile of 
the Scout vehicle. The motors are connected by transition sections. Table III 
lists the Scout stages. The air frame, base, and transition section composition 
are outlined in table IV. Figure 25 shows the various station locations. 

Structure Assembl ies 

Base A section (figure 25) is an aluminum, semi-monocoque cylindrical 
shell bolted to the rocket motor and enclosing the motor nozzle to form the 
aft end of the rocket vehicle. Incorporated in base A are four fixed fins 
equipped with movable control surfaces, a hydraulic system to operate the 
control surfaces, amplifiers for signals from the guidance system to the hydrau- 
lic actuators and telemetering components. The movable fin tip and a jet vane, 
immersed in the first-stage rocket motor exhaust area, are attached to each 
fin by means of a common torque tube. The torque tube, and consequently the 
attached fin and jet vane, is positioned by a servo actuator installed in each 
fin. Each servo actuator is powered by the hydraulic system and controlled 
through the guidance system to provide vehicle stabilization and guidance 
during lift off and first-stage motor firing. 

Transition B (figure 25) consists of upper B and lower B assemblies. Lower B 
forms the primary load path between the first and second stages of the vehicle. 
First stage to second stage structural mating is accomplished by utilizing 
the inner threaded surfaces of lower B and the second-stage motor nozzle. A 
threaded diaphragm is inserted into the threaded portion of lower B and then 
in turn into the motor nozzle. The first-stage motor is then mated to the aft 
end of lower B. Lower B contains the first-stage headcap pressure switch and 
the telemetry first-stage headcap pressure transducer. Removable panels 
provide access to the components. 



y^ 



(l)iiQii section was used with the five-stage Scout vehicles. 



ORIGINAL PAGE IS 
' OF POOR QUALITY 



\kk.i 




1 . _ 

|«- 118 



(All dimensions are in inches) 



Figure 23-- Sketch of Scout vehicle (Scout D-1). 



ORSQsl^AL PAGE SS 
28 OF POOR QUALITY 



TABLE 1 1 I - SCOUT STAGES 
SCOUT A-1, A-2, B-], B-2, D-1 AND F- 1 ^^ ' 

Stage Assembly 

1 Base A Section (includes fins and jet vanes) 
Algol lie Rocket Motor (A-1 and B-l) 

Algol II lA Rocket Motor (D-1 and F-1) 

Transition B - Lower (includes blowout diaphragm) 

2 Transition B - Upper 

Castor MA Rocket Motor (all configurations) 
Transition C - Lower (includes blowout diaphragm) 

3 Transition C - Upper 

Antares MA Rocket Motor (A-I, B-l, and D-1) 
Antares MB Rocket Motor (A-2, B-2, and F-1) 
Transition D - Lower 

Transition D - Center (includes spin bearing and 

separation system) 

4 Transition D - Upper 

Altai r II Rocket Motor (A-1 and A-2) 

Altait IMA Rocket Motor (B-l, B-2, D-1, and F-1) 

Heat Shield 

Transition E (includes cold separation system) 

5 Payload Assembly (may be used as part of fourth 

stage) 



SCOUT E-1 



1 Base A Section (includes fins and jet vanes) 
Algol IMA Rocket Motor 

Transition B - Lower (includes blowout diaphragm) 

2 Transition B - Upper 
Castor I lA Rocket Motor 

Transition C - Lower (includes blowout diaphragm) 

3 Transition C - Upper 
Antares MB Rocket Motor 
Transition D - Lower 

Transition D - Center (includes spin bearing and 

separation system) 

^ Transition D - Upper 

Altair I MA Rocket Motor 
Transition F - Lower 
Heat Shield 

5 Transition F - Upper 
Alcyone I A 

Transition G (includes payload separation system) 

6 Payload Assembly (mey be used as part of fifth 

stage) 



(1) 



Not used in Phase V I 



OR!G!MAL PAGE IS 
OF POOR QUALITY 




51 



0RIG3!^AL PMMi 63 
OF POOR QUALITY 



SECTION 



BASE A 



LOWER B 
UPPER B 

LOWER C 

UPPER C 

LOWER D 

MIDDLE D 

UPPER D 

BASIC E 

SERIES 200 E 

SERIES 25 E 

LOWER F 

UPPER F 

G 

HEAT SHIELD 



Heat 
Shield 



TABLE IV - BASE AND TRANSITION SECTION COMPOSITION, 



Aluminum semi-monocoque structure with steel fins and tip 
controls and 85/15 tungsten/molybdenum jet vanes through 
Phase Vl and copper infiltrated tungsten beginning with 
Phase VI I. 

Aluminum semi-monocoque structure. 

Laminated glass cloth with phenolic resin (not primary 
structure. 

Laminated glass cloth with phenolic resin (monocoque 
structure. 

Laminated glass cloth with phenolic resin (semi-monocoque 
structure. 

Steel and aluminum semi-monocoque structure. 

Aluminum monocoque structure. 

Magnesium monocoque structure. 

Magnesium casting. 

Magnesium casting. 

Magnesium monocoque structure. 

• (1)1 
i lum. ^ ■' 

(1) Not used in Phase VI. 



Magnesi 



Magnesium. 
Magnesium. 



(1) 



0) 



Laminated glass honeycomb with phenolic resin and 
Inconel nose cap. 



< 



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131.9 
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437.6 



Minus I Plus 
Station Station 
Locations Locations 



I 

809.9 

8'«7;95 
All dimensions are in inches. 



t>RECEDlNG PAGE BLANK NOT FILMED 



Figure 25.- Various Station Locations Along the Scout Vehicle. 



32 



Upper B is constructed of two glass-laminated clamshell sections which bolt 
to the second-stage rocket motor and enclose the motor nozzle. Upper B con- 
tains four 40-pound roll motors, four 500-pound pi tch-and-yaw motors, a 
hydrogen peroxide supply for activating the motors, a nitrogen supply for 
pressurizing the hydrogen peroxide, and telemetry components. Removable 
panels provide access to components. 

Transition C (figure 2$) is divided into upper C and lower C at the frangible 
diaphragm. The aft end of lower C bolts to the forward end of the second- 
stage rocket motor. The forward end connects to the aft end of upper C by 
means of the frangible diaphragm to provide stage separation at third-stage 
motor ignition. Lower C contains an ignition arming relay, second-stage head- 
cap pressure switch, and the telemetry second-stage headcap pressure transducer. 
Removable panels provide access to the interior components. 

Upper C is a slightly tapered cylindrical structure having an aluminum and 
phenolic glass framework covered with phenolic glass. The forward end bolts 
to the aft end of the third-stage rocket motor case and the inside aft end 
is threaded and connects to lower C by means of the frangible diaphragm. 
Upper C contains ignition batteries, guidance rate gyros, diode unit, reaction 
control fuel and motor system, command destruct receiving and initiating system, 
and telemetering components. Removable panels provide access to interior 
components . 

Transition D (figure 25) is divided into upper D and lower D at the spin 
bearing. The aft end of lower D bolts to the third-stage rocket motor and 
the forward end supports the spin bearing. Lower-D section contains ignition, 
guidance and telemetering components, including such components as a guidance 
programer, inertia) reference package, poppet valve electronics, intervalometer , 
inverter, telemetering package, F/M transmitter, and radar beacon. The inner 
surfaces of the section are coated with mirror-like gold finish to provide 
emissivity for thermal protection of the components. Removable panels provide 
access to components. 

Upper D is divided into two sections at the mating plane of the third and 
fourth stages and is held together by an explosive bolt-secured clamp which 
provides stage separation. The lower section contains four rocket spin 
motors and its aft end is attached to the spin bearing. The upper section 
bolts to the fourth-stage rocket motor. The upper section has an optional 
system for measurement of vehicle fourth-stage performance and a complete 
dualized separation system. Upper D is covered by the heat shield when the 
vehicle is assembled. 

Four standard pavload-to-vehicle adapter sections. Section "E," Series 200 "E," 
Series 25 "E,"(^5 and Section "E-G"(1) are available for mating a payload to 
the fourth-stage motor. The selection of a standard adapter is contingent on 



TO 



Not used on Phase VI vehicles. 



33 

payload weight and center-of-grav i ty location. It sinould be noted that the 
weight capability of the adapter section includes the weight of both the 
adapter section and the spacecraft. The rated load-carrying capability of 
each adapter section is based on structural load tests. Figure 26 shows the 
payload weight capability for each standard adapter when the payload center 
of gravity is located at vehicle station Ik, The payload weight capabilities 
of the adapter section at other center-of-grav ity locations are shown in 
figure 27. 

The basic adapter assembly consists of a conical adapter, a payload support 
ring and a payload separation clamp. The adapter base is bolted directly to 
the final-stage motor forward flange. The payload support ring provides 
threaded holes for attachment to the payload and machined surfaces for mating 
to top of adapter. The payload separation clamp is a two-piece assembly. 
When bolted together, this clamp holds payload support ring and adapter together, 
The clamp configuration allows removal of the payload from the vehicle. The 
separation system springs provide sufficient energy to impart a relative sepa- 
ration velocity of 3-^ feet per second to a 200-pound spacecraft. 

The standard adapter sections are designed to provide a separation system when 
required and to satisfy a mandatory requirement for access to the final-stage 
motor igniters. In general, the design of the standard adapter/separation 
system is basically the same for all sections. 

Transition "E-G" is available, as an option, to attach the payload to the 
fourth-stage motor and to provide for payload separation. The "E-G" section 
is used for light weight pay loads. Transition "E-G" incorporates the aft ring 
of trans it ion"E"and the forward ring of trans it ion"G ." (Not used in Phase VI.) 

Transition "F" includes the fifth-stage separation system and is used only 
when a fifth stage is required. 

Transition "G," which will include the payload separation system, is used with 
five-stage vehicles only. 

The heat shield (figures 28 and 29) covers the payload, fourth-stage motor, and 
upper-D section, and is designed to maintain the enclosed components within 
specified temperature limits. The Scout vehicle has used heat shields having 
a diameter of 20 inches, 21.5 inches, 25.7 inches, 3^ inches, and k2 inches, 
with only the 3'+-!nch and 42-inch diameter heat shield now available. 
Figure 28 shows a typical heat shield and the heat-shield history through 
Phase VI. Heat shields are fabricated from two fiber glass honeycomb half- 
shells. The 34-inch diameter heat shield has a stainless steel nose cap and 
the 42- inch diameter heat shield has a cork-covered aluminum nose cap. The 
nose cap attaches to one half-shell and butts against the other half-shell. 
The 34- inch heat shield has a body section outside diameter of 34 inches, tapers 
to 25.7 inches at the aft end and extends to forward nose station -25 or -40. 
A 22-degree conical section supports the 7-71-inch radius nose cap. The 42-inch 



rfii 1'3 



Of pOGU Q->^^*-'' 



34 




STA 
47.77) 



SPACECRAFT 



ADAPTER 
SECTION 



4TH stage! 
MOTOR 



PAYLOAD WEIGHT = A 



+ B 



400 



350 



300 



250 

PAYLOAD 
(A + B) 

WEIGHT 200 
IN 

KILOGRAMS 
150 



100 




20 25 30 35 
VEHICLE STATION 



Figure 26.- Allowable payload weight and C.G. locat 



ion, 



35 



0RIG2MAL PAGE IS 
OF POOR QUALITY 




100 200 

PAYLOAD WEIGHTS - KG 



300 



Figure 27-- Payload Weight Capability of Adapter Sections, 



36 



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37 





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38 

heat shield has a body section outside diameter of 42 inches, tapers to 28.2 
inches at the aft end and extends forward to nose station -kS . Figure 29 
illustrates the comparison of the 34-inch and 42-inch heat shields. A 
12.5-degree conical section supports a 12.28-inch spherical radium nose cap. 
Figure 30 shows an explosion view of Scout. 

WEIGHT 

The Scout D-1 vehicle has a nominal lift-off weight of approximately twenty- 
five tons. Nominal weight summaries for Scout configurations are given in 
tables V-Vill. Appendix B gives a more detailed weight breakdown. The stage 
weights shown include those parts of the transition section which remain 
attached to the stage upon separation from the previous stage. The consumed 
weights shown for the second and third stages include nominal amounts of 
hydrogen peroxide used by the reaction control system. The final weight of 
the vehicle is dependent upon the weight of the payload. Figure 31 shows 
Scout vehicle S-192C ready for launch. 

LOADS 

The largest transverse flight loads on a vertically-rising launch vehicle 
structure are produced by horizontal wind and gusts. Vehicle flight loads are 
shown in figure 32. Scout S-133 was instrumented as shown in figure 33 for 
the purpose of measuring these winds, gusts, and control commands. The 
measured wind and gust profiles were used as disturbances in an analytical 
simulation program to calculate the vehicle motions and loads. v^) This is 
typical of the testing and research accomplished on all Scout systems. Vehicle 
ground handling loads are shown in figure 34. 

Typical flight loads for a four-stage Scout launched from Wallops Flight Center 
into a 300-nautical mile easterly circular orbit with a 377-pound payload has 
maximum axial acceleration of 9.5 g's at about 130 seconds, 166 seconds, and 
620 seconds consecutively after first-stage ignition. The axial acceleration 
also peaks to 417 g's at about 55 seconds after ignition. 

The second peak of 166 seconds complements the velocity which also peaks at 
166 seconds which coincides with third-stage burnout. The inertial velocity, 
at this point, reaches 3|240 nautical miles per second. 



^ ^Scout vehicle flight loads were presented to the AlAA structural dynamics 
and aeroelast icity conference by K. G. Pratt and H. C. Lester. 



ORIGf(\?AL PAQ5? ^3 
OF POOR QUALITY 



39 




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40 



ORIGINAL PAQE S3! 
OF POOR QUALITY 



TABLE V - NOMINAL VEHICLE WEIGHTS 

SCOUT A-1 
Algol llC/Castor I I A/ An tares IIA/Altalr I lA 



EVENT 


WEIGHT, POUNDS 


'»2-45 
Heatshield 


3^-^0 
Heatshield 


34-25 
Heatshield 


Payload 


0.00 


0.00 


0.00 


^tth Inert 


102.99 


102.99 


102.99 


^tth Burn-out 


1 02 . 99 


101.99 


102.99 


Ath Consumed 


510.04 


510.04 


510.04 


4th Ignition 


613.03 


613.03 


613.03 


3rd Inert 


7^9.33 


7'*9.33 


749.33 


3rd Burn-out 


1 362 . 36 


1362.36 


1362.36 


3rd Consumed 


2593-81 


2593.81 


2593.81 


3rd Ignition 


3956.17 


3956.17 


3956.17 


2nd Inert Less Heatshield 


2052.68 


2052.68 


2052.68 


2nd Inert 


2A04.26 




23^48.51 


2312.26 


2nd Burn-out 


6360.^3 


630A.68 


6268.43 


2nd Consumed 


8307. A2 


8307. A2 


8307.42 


2nd Ignition 


IA667.85 


14612.10 


14575.85 


1st Inert 


3425.3'* 


3391.50 


3391.50 


1st Burn-out 


18093.19 


18003.60 


17967/35 


1st Consumed 


21385.00 


21385.00 


21385.00 


1st Ignition 


39^78.19 


39388.60 


39352.35 



k\ 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLF VI - NOMINAL VEHICLE WEtGHTS 

SCOUT B-1 
Algol llC/Castor I I A/An tares IIA/Altair MA 



Pay load 



4th Inert 



3rd Burn-out 



3rd Consumed 



3rd Ignition 



EVENT 



4th Burn-out 
4th Consumed 
4th Ignition 
3rd Inert 



2nd Inert Less Heatshield 



2nd Inert 



2nd Burn-out 
2nd Consumed 
2nd Ignition 



1st Inert 



1st Burn-out 



1st Consumed 



1st Ignition 



42-45 
Heatshield 



0.00 



94.35 



94.35 



604.44 



698.79 



749.33 



1448.12 



2593.81 



4041.93 



2052.68 



2404.26 



6446.19 



8307.42 



14753-61 



3425.34 



18178.95 



21385.00 



39563.95 



WEIGHT, POUNDS 



34-40 
Heatshield 



0.00 



94.35 



94.35 



604.44 



698.79 



749.33 



1448.12 



2593.81 



4041.93 



2052.68 



2348.51 



6390.44 



8307.42 



14697.86 



3391.50 



1 8089. 36 



21385.00 



39474.33 



34-25 
Heatshield 



0.00 



94.35 



94.35 



604.44 
698.79 
749.33 



1448.12 



2593.81 



4041.93 



2052.68 



2312.26 



6354.19 



8307.42 



14661.61 



3391.50 



18053.11 



21385.00 



39438.11 



k2 

TABLE VII - NOMINAL VEHICLE WEIGHTS 

SCOUT D-1 
Algol IIIA/Castor I lA/Antares IIA/Altair IMA 



EVENT 


WEIGHT, POUNDS 


42-45 
Heatshileld 


34-40 
Heatshield 


34-25 
Heatshield 


Pay load 


0.00 


0.00 


0.00 


Ath Inert 


94.35 


94.35 


94.35 


4th Burn-out 


94.35 


94.35 


94.35 


4th Consumed 


604.44 


604.44 


604.44 


4th Ignition 


698.79 


698.79 


698.79 


3rd Inert 


749.33 


749.33 


749.33 


3r'd Burn-out 


1448.12 


1448.12 


1448.12 


3rd Consumed 


2593.81 


2593.81 


2593.81 


3rd Ignition 


4041.93 


4041 .93 


4041.93 


2nd Inert Less Heatshield 


2052.68 


2052.68 


2052.68 


2nd Inert 


2404.26 


2348.51 


2312.26 


2nd Burn-out 


6446.19 


6390.44 


6354.19 


2nd Consumed 


8307.42 


8307.42 


8307.42 


2nd Ignition 


14753.61 


14753.61 


14753.61 


1st Inert 


4260.54 


4226.70 


4226.70 


1st Burn-out 


19013.70 


18979.86 


18979.86 


1st Consumed 


28181.13 


28181.13 


28181.13 


1st Ignition 


47194.83 


47160.99 


47160.99 



43 



ORiGiJ^AL PPJM IS 
OF POOR QUALITY 



TABLE Vm - NOMINAL VEHICLE WEIGHTS 

SCOUT E-1 
Algol IIIA/Castor IIA/Antares IIB/Altalr IIIA/Alcyone lA 



EVENT 


WEIGHT, POUNDS 


42-45 
Heatshield 


34-40 
Heatshield 


34-25 
Heatshield 


Payload 


0.00 


0.00 


0.00 


5th Inert 


32.92 


32.92 


32.92 


5th Bum-out 


32.92 


32.92 


32.92 


5th Consumed 


194.42 


194.42 


194.42 


5th Ignition 


227.34 


227.34 


227.34 


4th Inert 


103.34 


103.34 


103.34 


4th Burn-out 


330.68 


330.68 


330.68 


4th Consumed 


604.44 


604.44 


604.44 


4th Ignition 


935.12 


935.12 


935.12 


3rd Inert 


• 753.07 


753.07 


753.07 


3rd Burn-out 


1688.19 


1688.19 


1688.19 


3rd Consumed 


2579.37 


2579.37 


2579.37 


3rd Ignition 


4267.56 


4267.56 


4267.56 


2nd Inert Less Heatshield 


2052.68 


2052.68 


2052.68 


2nd Inert 


2404 . 26 


2348.51 


2312.26 


2nd Burn-out 


6671.82 


6616.07 


6579.82 


2nd Consumed 


8307.42 


8307.42 


8307.42 


2nd Ignition 


14979.24 


14923.49 


14887.24 


1st Inert 


4260.54 


4260.54 


4260.54 


Ist Burn-out 


19239.78 


19184.03 


19147.78 


1st Consumed 


28181.13 


28181.13 


28181.13 


1st Ignition 


47420.91 


47365.16 


47328.91 











ORIGINAL PAGE B 
kk OF POOR QUALITY 




Figure 31-- Launch of S--192 frofi": WTR 



45 



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Figure 34.- Vehicle ground handling loads (ultimate) 



^9 



CHAPTER I I I - PROPULSION 



...-ocniMG PAGE 
('tit'-"—" 



BUAMK NOT FILMED 



50 



The physical data of the rocket motors are itemized in table IX. 
TABLE IX - ROCKET MOTOR PHYSICAL DATA 



Stage 

First 

First 

Second 

Third 

Third 

Third 

Fourth 

Fourth 

Fifth 



Motor 

Algol lie 
Algol lllA 
Castor I lA 
Antares 1 lA 
Antares MB 
Antares IMA 
Altair MA 
Altair IMA 
Alcyone 



Diameter, In, 

ko 

kk 
31 
30 
30 
30 
18 
20 
18.25 



Weight, Lb. 

23.674 

31,271 

9,760 

2,800 

2,789 

3,072 

577 

662 

216 



Nominal motor data for the four rocket motors of Scout B are shown in 
figure 35 and table X which show vacuum thrust and consumable weight as 
functions of burning time. Pref 1 ight trajectory calculations are made 
using motor data predictions based on specific vehicle motors. The deviation 
in performance resulting from the use of actual instead of nominal motor data 
is not expected to exceed tS pounds of pay load. 

The Algol MB or Algol MC Scout first-stage propulsion unit was produced by 
the Aerojet General Corporation, Sacramento, California. The Algol MC has 
an improved nozzle. The original Scout vehicles used an Algol ID for the 
first stage. The Algol MA was incorporated into the Scout system in 
February 1963 and the Algol I IB was first used in the Scout system in 
October 1964, The Algol Ml was developed by United Technology Center at 
Sunnyvale, California, and is the current standard first stage. The first 
launch of this motor was November 16, 1972. 

Below is the major Scout Algol motor history. 

Program initiated in 1957 under NASA contract 

First Algol I launch on Scout - 4-18-60 

First Algol I Scout launch on ST-1 7-1-60 

Changed propel lant, designated Algol MA - 1962 

Failure of MA nozzle, vehicle S-MO 7-20-63 

Nozzle redesign, designated Algol MB - 1964 

First Algol MB launch on ST-140C - 12-12-65 

Thirty-six successful flights with Algol I IB configuration 

Nozzle anomaly on vehicle S-160 - 1968 

Edler nozzle rework program - 1 968-1 969 

Propel lant igniter development - 1969 

Qualified vertical batch mix - 1969 

Extended shelf life to four years - 1970 

Qualified ablative Algol MC nozzle - 1970 

Five successful flights with Algol MC configuration 

Extended shelf life to five years - 1970 

First launch Algol MC on S-166 - 9-20-71 



51 



ORiGirmL PAQE [S 
OF POOR QUALITY 



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52 



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5k 

manufactured at the Bacchus Works of Hercules Incorporated in Magna, Utah, The 
CH-iginal Scout used a\n X-254 rocket motor also designed for Scout by scaling down 
an X-248. Below As the major Scoot X-259 Motor history: 

• Program initiated in I96I under Navy contract 

• First X-259 launch on Scout ST-9 in I962 

• Squib SD6OEO replaced SD55A3 

• Shelf life extended to ^3 months in I966 

• Igniter configuration improved 

• Changed from Epi rez/Epicure case-bond system to Epon 9^6 

• Vehicle S-152 failure in I967 due to case burn-through (X-259 with 

Epirez/Eplcure) 

• Shelf life reduced to 17 months in 196? 

• Thirty-six successful flights with Epon 9^6 bond system since 

vehicle S-152 failure 

• Shelf life increased to Ik months in I968 

• Shelf life extended to 36 months in 1969 

• Shelf-life program initiated in 1970 - increased to k^ and kk months, 

igniter extended to 72 months in 1971 

• Shelf life extended to 60 months 

• New production motors changed to high pressure operation incorporating 

lightweight igniter, new nozzle throat material, and SBASI initiator 
(replacing SD6OEO) . A quality assurance motor was fired at simulated 
altitude conditions and demonstrated a 1.5 percent improvement in 
delivered specific impulse and total impulse (Figure 36.) 

• Shelf life of motors extended to 8k months, conventional igniters to 

86 months in 1973 

• First flight of X-259B4 (high pressure) motor on Scout vehicle S-I9I 

in 197^ (figure 7 shows Scout S-I9I ready for launch) 

• First demonstration of Trident program propel lant in X-259 motor 

resulted in nozzle failure in 197^- Nozzle design was modified 
for second demonstration test 

• Motor shelf life extended to 96 months in 1975 

• Shelf life program to continue - goal is ten years 

• Two successful launches with high pressure X-259B4 motors were Scout 

vehicle S-191 in 197^ and S-19't in 1975 

• Last launch of high pressure X-259B4 on Scout vehicle S-I96 on Decem- 

ber 1975 resulted in a nozzle burn through 

• Motor shelf life extended to 108 months in 1977 

The Antares I ! lA rocket motor (TEM-762) was developed and qualified and is in 
production by the Thiokol Corporation, Elkton Division, Elkton, Maryland. The 
motor was incorporated into the Sc^ut system in 1978 to be interchangeable 
with the Antares II. It was originally planned to provide a 40-pound payload 
improvement but the qualified design provided 57 pounds payload gain in 300 
nautical mile orbit launched east from Wallops Flight Center. Below is major 
Scout Antares IMA motor list. 

• Design, development, qualification during 1977-1979, shelf life 

established at 6O months 

• First Antares MIA launch on S-203 in 1979 using new nozzle throat 

material (4-D carbon/carbon) being flown for first time on any rocket 
motor . 



53 

• First launch Algol I I I on S-184C - 8-13-72 

• Burst test Algol II I - 1973 

• Three-year shelf life for Algol III verified in 197^; shelf life program 

continuing - goal 10 years 

• Extended shelf life to sixty-six months - 1975 

• Program initiated to extend shelf life of Algol IIC to nine years - 

ultimate goal is ten years - 1975 

• Severe degradation of the motor bond system was experienced after nine 

years. A subsequent decision was made not to fly Algol IIC motors 
on Scout 

United Technology Center was awarded contract in 1969 to produce Algol III motors 
(45-inch diameter compared to 40-inch diameter Algol I and II). Development and 
qualification consisted of five static firings. Twenty Algol Ill's have been 
launched and have performed successfully in flight. The twentieth was S-192, 
the last Phase VI launch. Figure 31 shows Scout vehicle S-192, the fifteenth 
and last Phase VI vehicle. 

The Castor II rocket motor, present second-stage Scout propulsion unit, is 
manufactured by Thiokol Chemical Corporation, Redstone Division, Huntsville, 
Alabama. The original Scout vehicles used a Castor I for the second stage. The 
Castor MA was incorporated in the Scout system in August 19^5 as shown in 
figure k. Below is the major Scout Castor motor history. 



• 



Castor I program initiated in 1957 under Army contract 



• First Castor I launch on Scout ST-1 in I96O 






Castor II program initiated in I963 under NASA contract 
First Castor II launch on Scout S-I3I in 19^5 
Propellant changes in I966 to improve physical properties 
Pyrogen case changed from glass to steel in 1969 - 

simplicity and cost advantage 
Shelf life study in I969 - increased to 36 months 
Shelf life program in 1970 - increased to 48 months 



• Shelf life extended to 60 months in I972 



• 






Aging tests in 1974 of Thixon AB-894 primer coat for bonding insulator 
to Castor MA case confirmed no degradation after two years; 4-year 
tests were conducted in 1976 

Shelf life extended to 72 months in 1975 

Shelf life program expanded to extend to 84 months; ultimate goal is 
ten years 
• Current Castor MA motor shelf life is IO8 months (9 years) - I98I 

Currently (I98I) there are ten Algol IMA motors in production, scheduled for 
completion in January I982. This will add to the five Algol IIIA's already in 
Scout inventory for a total of fifteen Algol lllA's. 

The Antares rocket motor (X-259) was designed specially for the NASA Scout 
third stage by Hercules Powder Company at their Allegany Ballistics Laboratory, 
Cumberland, Maryland. The Antares X-259 's an improved version of the X-254 
which was used on the original Scout vehicles. The X-259 was incorporated 
into the Scout system in March 1962 as shown in figure 4. This motor was 



55 




4) 

E 

JZ 

O 



c 



o 
*-> 

O 
E 

4-1 

<u 

u 
o 



m 
CD 

m 

+-> 

< 






3 



ORIGINAL PAGE 
BLACK AND WHITE RHOIOGRAEH 



56 



First production motor delivered in I98O 
Second Antares IMA launch on S-192 in I98I 



CU' 



PC-::^ QUALITY 



The Altair 11 rocket motor (X-258) , Scout system upper-stage propulsion unit, 
is manufactured at the Allegany Ballistics Laboratory. This motor has replaced 
the Altair I (X-248) which was used on the original Scouts. The X-258 was incor- 
porated in February I963 as shown in figure k. The X-258 has been phased out 
on all NASA missions and has been replaced by the Altair III (FW-4S) . 

Below is the major Scout X-258 motor history. 

• Program initiated in ^^6^ under Navy contract 

• First X-258 launch on vehicle S-113 in 1963 

e Reinforced rod and cusp incorporated into igniter design due to inability 

to properly ignite X-258 motor 
Shelf life extended to 15 months in 1 966 
Squib SD6OAI replaced SD6OAO 
Shelf life extended to 17 months in I967 
Nozzle fabrication improved by use of Raybestos/Manhattan phenolic 

ring molding 
Shelf life extended to 2k and 36 months in I969 
Igniter shelf-life program initiated in 1970 
Shelf life of motor extended to 48 and 60 months in 1971 
Shelf life of igniter extended to 60 months in 1971 
Shelf life of igniter extended to 72 months in 1972 
Shelf life of motor extended to 72 months in 1973 
Shelf life of igniter extended to 90 months in 1973 
Shelf life of motor extended to 84 months in 1974 
Shelf life of Motor extended to IO8 months and igniter to 120 months 

in 1977 









The Altair III rocket motor (FW-4S) was first used as a fourth-stage motor in 
August 1965 as shown in figure 4. This DOD-developed rocket motor is produced 
by the United Technology Center at Sunnyvale, California. It has replaced the 
Altair II on all missions until replaced by the (tEM-640) Altair IMA qualified 
and manufactured by the Thiokol Corporation, Elkton Division, Elkton, Maryland. 
Below is the major Scout FW-4S motor history. 

Program initiated in 1964 under Air Force contract 

First FW-4S launch on Burner I in I965 

First Scout launch on vehicle S-I3I in 1965 

Interspersed filament winding of case implemented in I966 

Vehicle S-151 in 1967 failed due to nozzle problem 

Nozzle redesigned with backed-up ATJ throat 

Four remaining 1967 launches successful with ATJ 

Nozzle further improved with Graphitite G manufactured in I963 

Shelf life program initiated in 1 969 - increased motor shelf life to 

17 months and igniter shelf life to 22 months 
Shelf life increased to 36 months in 1970 for both motor and igniter. 
Motor shelf life extended to 42 months and igniter shelf life to 

60 months in 1971 



57 



• Motor shelf life extended to 60 months in 1972 



• 






e 



New contract for Altair I I |A (TEM 640) was awarded to Thiokol's 

Elkton Division. A demonstration motor was successfully fired by 

Thiokol in 1972 (Figure 37 shows the launch of Scout vehicle S-I89 

which flew the first (TEm GkO) 
Thiokol experienced three qualification motor failures in 1973 
UTC was awarded back-up contract for FW-4S f 1 ight motors because of 

Thiokol problems; UTC quality assurance FW-4S motor exceeded safe 

operating temperature in simulated altitude test; UTC contract was 

canceled. 
Thiokol fired two successful static test motors and two successful 

quality assurance motors in 1974; fourteen Thiokol TEM 640 motors 

have been successfully flown on Scout 
Thiokol successfully demonstrated advanced higher energy propel lant 

in Altair I NA configuration in 1974 
UTC and Thiokol demonstrated use of SBASi as initiator for Altair 

in 1974 
UTC has unsuccessfully demonstrated an advanced high energy propel lant 

in Altair MIA configuration 
Thiokol continued an advanced propel lant program in 1975 
Shelf life for tEM-640 (Altair IMA) established in 1972 at 72 months, 

with a supporting program; ultimate goal is 10 years 



The Alcyone rocket motor (BE3-A9) was developed as a fifth stage for the Scout 
vehicle and was manufactured by the Bacchus Works of Hercules Incorporated in 
Magna, Utah, Below is the major Scout Alcyone motor history: 

• Shelf life of BE3-A9 was established at 36 months in I968 

• Shelf life extended to 96 months in 1973 

• The first and only flight BE3-A9 was flown on Scout S-I9I in 1974 and 

performed successfully 

Table XI is a summary of the Scout motor shelf life. Table XII lists the 
serial numbers and configurations of the Scout vehicle rocket motors launched 
in Phases Vl and Vll. Table XV lists the inventory remaining for Phases Vll 
and VIM. The heat shield covering the top stage motors and the E-Sections 
are also listed in these tables. 

The technical data for the above listed propulsion systems are detailed in 
figures 38 through 46. Tables XV I through XXV itemize the history of each 
motor stage. Designated is the serial number, the contract that the motors were 
purchased on, and the use made of the motor; such as used for testing or launched 
with vehicle number... The tables are divided as follows: 

XVI - Algols I and Algols I I 

XV II - Algol III 
v\; I I I _ r^<- 1-^^ I 

XIX - Castor I I 

XX - Castor I |A 

XXI - Antares I lA and I IB 

XXI I - Antares I I lA 

XX II I - Altair il and Alcyone 

XXIV - Altair III 

XXV - Altair I I IA 



58 



ORIGINAL PAGF 
BLACK AND WHITE PHOTOGRAPH 



TABLE XI - MOTOR SHELF LIFE SUMMARY 



SHELF LIFE (YRS) 



MOTOR 

ALGOL I I 
ALGOL I I I 
CASTOR I I 
X-258 

ANTARES I lA 
ANTARES MB 
ANTARES I I lA 

BE-3 
ALTAIR IMA 



PRESENT 


TARGET 


8 


10 


5 


10 


9 


10 


9 


10 


9 


9 


9 


10 


5 


10 


8 


10 


6 


10 



REMARKS 

AM inventory over age. 

Lab testing continuing on periodic basis 

Annual specimen testing. 

No flight motors in inventory. 

None. 

None . 

Annual lab testing and test fire motor 
at 4 or 5 years . 

None. 

Sample testing in 1982 at 8^ years. 
Igniter tests in 1983 of 1975 loads. 




Flnuit: ^7.- ANS-A niiision on S-I89 showing the Scout corsplsx ai WTR . 











0R8G 


mM. FAGE IS 










OF POOR QUALITY 

59 






TABLE XII- HISTORY OF MOTORS AND HEAT SHIELDS USED ON SCOUT 






PHASES 


i, II, III 






PHASE VphirlP 


■First Staqe 


Second Staqe 


Third Staqe 


Fourth Staqe 


Shield 


/X 


1A3 


Dummy 


X254A1YS29 


None 


X 




STI 


1B6 


XM33E5-77 


X254A1YS30 


X248A5SV83 


1 




ST2 


189 


XM33E5-82 


X254A1YS41 


X248A5SV93 


2 




ST3 


1B7 


XM33E5-83 


X254A1YS48 


X248A5SV86 


3 


1 < 


STk 


1C23 


XM33E5-92 


X254A1YS50 


X248A5SV118 


4 


ST5 


IBIO 


XM33E5-326 


X254A1YS59 


X248A5SV112 


5 




ST6 


ICll 


XM33E5-108 


X254A1YS47 


X248A5SV178 


6 




ST7 


1C24 


XM33E5-124 


X254A1YS63 


X248A5BS851 


7 




ST8 


1C26 


XM33E5-125 


X254A1YS67 


X248A5SV190 


8 


^ST9 


1C27 


XM33E5-128 


X259A3HPC17 


X248A5BS8214 


9 




f 110 


11A14(1) 


XM33E5-155 


X259A3HPC110A 


X248A6BS8439 


114 




111 


1D29 


XM33E5-147 


X259A3HPC16 


X248A58SB217 


111 




112 


lD-AF-1 


AFXM33E5-175 


X259A3HPC25 


M2 


112 




113 


11A13 


XM33E5-143 


X259A3HPC128 


X258B1RH48 


A4 




114 


11A5 


XM33E5-149 


X259A3HPC105 


X248A5BSB255 


110 




115 


11A6 


XM33E5-153 


X259A4HPC119 


X248A5BSB256 


113 


>> { 


116 


11A8 


XM33E5-181 


X259A3HPC106 


X248A6BS8423 


A5 


117 


lD-AF-2 


AFXM33E5-I76 


X259A3HPC24 


M2 


117 




118 


11A4 


XM33E5-150 


X253A3HPC108 


X248A58SB240 


116 




119 


11A7 


XM33E5-154 


X259A3HPC117 


AFX248A5BS8223 


Al 




120 


11A12 


XM33E5-148 


X259A3HPC122 


X248A5BS8254 


A3 




121 


lD-AF-3 


AFXM33E5-177 


X259A3HPC26A 


M2 


121 


i 122 
^123 


11A21 (1) 


XM33E5-152 


X259A3HPC134 


X25881RH61 


AI3 


11829 


XM33E5-1B4A 


X259A3HPC143 


X258C1RH72 


A2 


/ 124 


11826 


XM33E5-252 


X259A3HPC130 


X258C1RH64 


129 




125 


11A24 


XM33E5-1B2 


X259A3HPC146 


X258C1RH55 


A8 




126 


11A9 


XM33E5-158 


X259A3HPC112 


M2 


126 




127 


11A16 (1) 


XM33E5-183 


X259A3HPC109C 


X248A58SB407A 


A7 




128 


11A22 


XM33E5-I80 


X259A3HPC132 


X258CIRH66 


All 




129 


11827 


XM33E5-159 


X259A3HPC136A 


X258C1RH70 


a6 


Mi i 


130 


11830 


XM33E5-422 


X259A3HPC157 


None 


A12 


131 


11836 


TX354-11A-23 


X259A3HPC160 


FW4S- 20038 


A27 (2) 




132 


1D33 


XM33E5-160 


X259A4HPC118 


X25881RH53 


CI 




133 


11832 


XM33E5-179 


X253A3HPC139 


X258C2RH73 


124 




134 


11825 


XM33E5-188 


X259A3HPC145 


X258C1RH68 


A9 




135 


11833 


XM33E5-423 


X259A3HPC159 


X258C2RH74 


A21 




136 


11828 


XM33E5-185A 


X259A3HPC166 


X258C3RH81 


A23 


\137 


11834 


XM33E5-161 


X259A3HPC167 


X258C1RH75 


AI5 




CONTRACTS - MOTORS 











First Stage - NAS5-53, 



NASI -585, NASI -1330, NASI -3833 

L93419, L2061, NASI -5034 



Second Stage - L55931, L77203, L93419, L2061 , NASI -5034 
Third Stage - SIOIO, L89844, L86693, L93985, L3420, NASI -3493 
Fourth Stage - SIOOO, L72505, L89844, L93985, L2570, L6990, NASl-3664, 
NASI -3698 



NASI -3698 

(1 )Hard core Algol . 

(2)0nly payload separation system supplied by Scout-n 



60 



ORIGINAL Pli 






IS 



OF POOR QUALITY 



TABLE XIII - HISTORY OF MOTORS AND HEAT SHIELDS USED ON SCOUT PHASES 



IV / 



PHASE VEHICLE 



138 
139 
140 

146 

148 

149 

150 

151 

152 

153 

154 

155 

156 

157 

158 

159 

160 

161 

162 

163 

164 

165 

166 

167 

168 

169 

170 

171 

172 

173 

174 

175 

176 

177 



FIRST STAGE 

IIB35 

IIB37 

IIB38 

IIB40 

IIB44 

IIB4I 

I IB 77 

IIB43 

IIB45 

IIB50 

IIB39 

IIB48 

IIB47 

IIB42 

IIB49 

IIB46 

ilB5l 

IIB52 

IIB56 

IIB53 

IIB57 

IIB54 

1 1 862 

IIB59 

IIB58 

IIB69 

IIB65 

IIB73 

lie 71 

IIB64 

IIB60 

IIB67 

1 1 1-5502-1 

1 1 872 

IIB63 

11874 

IIB68 

11866 

11875 

11876 



SECOND STAGE 

XM33E5-178 

XM33E5-I89 

TX354-IIA-24 

XM33E5-190 

TX354-IIA-17 

TX354-IIA-16 

TX354-IIA-I85 

TX35't-IIA-20 

TX354-IIA-I8 

TX354-IIA-19 

TX354-IIA-21 

TX35'»-IIA-25 

TX354-IIA-27 

TX35'^llA-29 

TX354-IIA-26 

TX354-IIA-28 

TX354-IIA-98 

TX354-IIA-)00 

TX354-IIA-102 

TX354-IIA-96 

TX354-IIA-105 

TX354-IIA-101 

TX354-IIA-97 

TX354-IIA-103 

TX354-IIA-170 

TX354-IIA-178 

TX354-IIA-174 

TX354-IIA-172 

TX35't-IIA-l83 

TX35'*-IIA-173 

TX354-IIA-104 

TX354-IIA-I71 

TX354-IIA-195 

TX354-IIA-176 

TX354-IIA-I79 

TX354-IIA-I82 

TX35't-IIA-l75 

TX354-IIA-J80 

TX354-IIA-184 

TX354-IIA-181 



THIRD STAGE 

X249A3HPC154 

X259A3HPC165 

X259A3HPC173 

X259A3HPC172 

X259A3HPCI69 

X259A4HPC170 

X25983HI8225 

X259A3HPC174 

X259A3HPC164 

X259A3HPCI61 

X259A3HPC183 

X259A3HPC177 

X259A3HPC181 

X259A3HPC184 

X259A3HPC151 

X259A3HPC182 

X259A3HPC163 

X259A3HIB202 

X259A3HI820I 

X259A3HIB220 

X259A3HPC2I2 

X259B3HI8205 

X25983HIB206 

X259B3HIB207 

X25983HIB213 

X259B3HIB305 

X259B3HI8209 

X259B3HIB2I5 

X259B3HIB30I 

X25983HtB2l6 

X259B3HI82I0 

X259B3HIB2I7 

X259B3HIB304 

X259B3HI8221 

X259B3HI82I4 

X259B3HIB224 

X259B3HIB2I8 

X25963HIB226 

X25983HI82I9 

X25983HIB223 



FOURTH STAGE 

X258E6RH125 

X258E6RHI26 

X258E6RH129 

X258E6RH1I7 

X258E6RH116 

X258E6RH118 

FW4S2223-8 

FW4S20031A 

X258E8RH)I0 

FW4S 20039 

FW4S30105 

X258E6RH136 

FW4S 30201 

FW4S30204 

FW4S30206 

FW4S30202 

X258E6RHI34 

X258E6ABLI43 

X258E6ABLI39 

X258E6RH135 

FW4S30210 

FW4$30207 

FW4S22I8-8 

FW4S22I8-I0 

X258E5ABL145 

FW4S2223-16 

NONE 

FW4S2223-4 

FW4S2223-11 

FW4S 2223-1 

FW4S2223-2 

FW4S2223-5 

FW4S2376-5 

FW4S2223-9 

FW4S2223-6 

FW4S2223-14 

FW4S2223-3 

FW4S2223-10 

X258E5ABL149 

FW4S2223-7 



IV AND V 

P/L SEP. 
SHIELD SYSTEM 



A-26 
A-28 

A-14 

A-24 

A-22 

A-31 

A-502 

A- 29 

A-32 

A-30 

A-33 

A-34 

A-35 

A-36 

A -40 

A-43 

A-37 

A-41 

A-39 

A-42R 

A-38 

A-25 

A-46 

A -49 

A-44 

A-400 

Non-Std 

A -47 

A-58 

A-45 

A -48 

A-53 

A-40I 

A -62 

A-56 

A-54 

A-57 

A-61 

A-55 

A-59 



E2P 

None 

N 

None 

N 

N 

E29 

E7 
N 

E8 

E9 

N 

E10 

Ell 

E18 

SM 

N 

E4 

N 
N 

E20 
None 

El 7 
E22 

N 

EG4 

. None 

E16 

None 

E19 

None 

E21 

GR 

SAS 

E34 

SM 

E35 
SAS 
N 
E37 



CONTRACTS 

First Stage - NAS 1-3833, NASl-5610 

Second Stage - NAS 1-5034. NASI -5883, NASI -56 10 

Third Stage - NAS 1-3493, NAS I -5883, NASI -56 10 

Fourth Stage - NASI -3698, NASI -5883, NASI -56 10 



61 



P,? -^is 



OF POOR QUALITY 



TABLE XIV - MOTORS ASSIGNED TO PHASES VI AND VII 

















HEAT 


P/L SEP. 


PHASE VEHICLE FIRST STAGE 


SECOND 


STAGE 


THIRD STAGE 


FOURTH STAGE 


SHIELD 


SYSTEM 


,178 1 


IC86 


TX354- 


1 IA-194 


X259B3HI310 


X258E5ABL150 


A50 


N 




179 1 


IC83 


TX354- 


IIA-193 


X259B3HI404 


TEM640-E21 


A409 


N 




180 1 


IC78 


TX354- 


1 IA-186 


X259B3HI314 


FW4S2223-15 


A60 


E36 




181 1 


11-5502-3 


TX354- 


IIA-191 


X259B3HI313 


FW4S2376-2 


A504 


E46 




182 1 


IC84 


TX354- 


IIA-197 


X259B3HI311 


FW4S2376-1 


A404 


N 




183 1 


IC89 


TX354- 


IIA-192 


X259B3HI302 


FW4S2223-12 


A63 


E31 




184 1 


11-5502-2 


TX354- 


IIA-187 


X259B3HI303 


FW4S2376-8 


A402 


MTS 


VI < 185 1 


11-5502-4 


TX354- 


1 IA-188 


X259B3HI312 


FW4S2223-13 


A403 


E45 




186 1 


1 1-5502-9 


TX354- 


1 IA-200 


X259B3HI315 


FW4S2376-6 


A507 


E49 




187 1 


IC79 


TX354- 


IIA-189 


X259B3HI307 


TEM640-013 


A505 


E204 




188 1 


11-5502-7 


TX354- 


IIA-198 


X259B3HI308 


FW4S2376-7 


A506 


E48 




189 1 


11-5502-10 


TX354- 


1 IA-201 


X259B3HI316 


TEM640-014 


A406 


E206 




190 1 


1 1-5502-6 


TX354- 


IIA-190 


X259B3HI306 


FW4S2376-4 


A66 


SM 


i 191 1 


11-5502-8 


TX354- 


IIA-199 


X259B4HI401 


FW4S2376-3(1) 


A405 


G102 


• 192 1 


II-5504-5P21 


TX354- 


1 IA-385 


X259E2 


TCC-E25 


A411 


N 


^-193 1 


11-5502-15 


TX354- 


1 IA-392 


X259B4HI405 


TEM640-E19 


A503 


E252 




194 1 


11-5502-11 


TX354- 


1 IA-390 


X259B4HI407 


TEM640-E16 


A508 


SAS 




195 1 


II-55D2-12 


TX354- 


1 IA-382 


X259B4HI309 


TEM640-E15 


A407 


N 




196 1 


11-5502-13 


TX354- 


1 IA-383 


X259B4hi406 


TEM640-E18 


A509 


El 54 


VII 1 


197 1 


11-5502-16 


TX354- 


IIA-196 


X259B4hi404 


TEM640-E1 7 


A408 


N 


) 198 1 


II -5504-2 PI 8 TX354- 


1 IA-394 


X259B4hi409 


TCC-E029 


A510 


E207 




200 1 


11-5504-1 PI 7 TX354- 


1 IA-393 


X259B4hi408 


TEM640-020 


A410 


E57 




201 1 


II-5504-4P20 TX354- 


1 IA-395 


X259B4hi411 


TEM640-E23 


A511 


E259 




202 1 


II-5504-6P22 TX354- 


1 IA-384 


X259B4hi412 


TCC-E027 


A513 






^203 1 


II-5504-7P23 TX354- 


1 IA-387 


TCC-I IIA-1 











TABLE XV - INVENTORY FOR BALANCE OF PHASE 


VII AND PHASE 


Vlll^^^ 




199 1 


II-5504-8P24 


TX354-IIA-391 


X259E3 


TCC-E31 


A- 52 


E261 


204 1 


II-5504-9P25 


TX354-IIA-386 


X259E4 


TCC-E32 


A-51 


E262 


205 1 


II -5504-1 0P26 


TX354-IIA-808 


X259E5 


TCC-E33 


A-416 


E263 


206 1 


ll-5504-np27 


TX354-IIA-809 


X259E6 


TCC-E34 


A-512 


E264 


207 1 


1 1 -5504-1 2P28 


TX354-IIA-810 


X259E7 


TCC-E35 


A-68 


E265 


(3)208 1 


11-5505-1(3) 


TX354-IIA-811 


BHI410 


TCC-E37 


A- 71 


E266 


209 1 


11-5505-2 


TX354-IIA-812 


BHI413 


TCC-E38 


A- 72 


E212 


210 1 


11-5505-3 


TX354-IIA-813 


b4h|414 


TCC-E39(3) 


A- 73 


EG6 


211 1 


11-5505-4 


TX354-IIA-814 


B4HI415 


TCC-E40 


A- 74 


G6 


212 1 


11-5505-5 


TX354-IIA-815 


X259E8(3) 


TCC-E41 


A-413 




213 i 


11-5505-6 


TX354-IIA-816 


X259E9 


TCC-E42 


A-41 5 




214 1 


11-5505-7 


TX354-IIA-817 


X259E10 


TCC-E43 


A-416 




215 1 


11-5505-8 (3)TX354-IIA-818 


X259E11 


TCC-E44 


A-41 7 




216 1 


1 1-5505-9 


TX354-IIA-819 


X259E12 


TCC-E45 


A-41 8 




217 1 


11-5505-10 


TX354-IIA-820 
TX354-IIA-821 


X259E13 
X259E14 
X259E15 


TCC-E46 


A-512 
A-514 
A-515 
A-516 
A-51 7 
A-518 
A-519 





(l)Fifth Stage BE3-003. 

(2) Inventory at time of publication (only flightworthy hardware listed). 

(3)Vehicle and motor listed and subsequent are being manufactured. Assignments are subject to change. 



PROPULSION SYSTEM 

ALGOL lie MOTOR DATA 



62 



OF POOR QUALITY 



The Algol IIC, Scout first-stage propulsion unit, is being produced by the 
Aerojet General Corporation, Sacramento, California. The Algol motor incor- 
porates a steel case and a lightweight reinforced plastic nozzle. The propel- 
lant grain is a tapered core, four-point star, internal burning configuration. 
The grain is a cast-in-case aluminized composite propel lant with a polyurethane 
binder. The igniter is a pelletized flame-producing rocket motor type, with 
dual squib initiators. This motor is being phased out in favor of Algol IIA. 



357.61' 




Total Impulse - Lb. - Sec. - Vacuum 


5,481,859. 


Specific Impulse - Lb. - Sec/lb. - Vacuum 


258.88 


Burning Time - Total - Sec. 


76.08 


Thrust - Avg. Web - Lbs. - Vacuum 


98,147. 


Weight - Total - Lbs. (Wt) 


23,799. 


Weight - Fuel - Lbs. (Wp) 


21,176. 


Mass Ratio - Wp/W^ 


0.89 


Nozzle Expansion Ratio 


7.36 


Weight Consumed - Lbs. 


21,392. 


Nozzle Exit Area - Ft.2 


5.67 



Figure 38.- First-stage propulsion unit used on Scouts A and B. 



L 



PROPULSION SYSTEM 



.J 



OF POOR QUALiTY, 



63 



The Algol MIA optional first-stage propulsion unit, is manufactured by United 
Technology Center (UTC) , a division of United Aircraft Corp., Sunnyvale, Cali- 
fornia. The Algol IIIA combines a steel motor case with a lightweight reinforced 
plastic nozzle. The propel lant grain is a tapered core, four-point star, 
internal burning configuration. The grain is a cast-in-case aluminized compos- 
ite propel lant with a polybutadiene acrylic nitrile binder. The igniter is 
a flame producing rocket motor type, with dual squib initiators. This motor 
had only been previously launched once in Phase V (S-170). 




Total Impulse - Lb. - Sec. - Vacuum 


7,200,000. 


Specific Impulse - Lb. - Sec/lb. - Vacuum 


258.2 


Burning Time - Total - Sec. 


78.0 


Thrust - Ayg. Web - Lbs. - Vacuum 


107,168. 


Weight - Total - Lbs. (Wt) 


31,165. 


Weight - Fuel - Lbs. (Wp) 


27,885. 


Mass Ratio - Wp/W^ 


0.895 


Nozzle Expansion Ratio 


6.48 


Weight Consumed - Lbs. 


28,135. 


Nozzle Exit Area - Ft.2 


5.67 



Figure 39.- First-Stage propulsion unit used on Scouts D and E. 



CASTOR II MOTOR DATA 



6k 



OF POOR QUAL5 



The Castor I lA rocket motor (TX-5^3-3) is the Scout second stage propulsion 
unit and is manufactured by the Thiokol Chemical Corporation. Huntsville 
Division, Huntsville, Alabama. The motor uses a steel case and an internally 
in.;..lated Steel nozzle. The nozzle and case serve as a structural member on 
Kelssembed Scout vehicle. The propellant charge is a polybutadiene acrylic 
actd (PBAA) binder system. The grain configuration consists of a cylind ical 
pa t with two radia/slots. The igniter is a rocket motor type (pyrogen) with 
dual squib initiators. This replaced the Castor 1 that was used on S-138, 139. 
and lUl. 



31.00' 




40.00" 



Total Impulse - Lb. - Sec. - Vacuum 

Specific Impulse - Lb. - Sec/Lb. - Vacuum 

Burning Time - Total - Sec. 

Thrust - Avg. Web - Lbs. - Vacuum 

Weight - Total - Lbs. (Wt) 

Weight - Fuel - Lbs. (Wp) 

Mass Ratio - Wp/W^ 

Nozzle Expansion Ratio 

Weight Consumed - Lbs. 

Nozzle Exit Area - Ft.2 



2,315,115. 
281.91 
38.97 
61,839. 
9,760. 
8,212. 
0.84 
20.95 
8,267. 
8.11 



Figure kO.- Scout second stage propulsion unit. 



ANTARES IIA MOTOR DATA 



65 



ORIGIMAL PASS :S 
OF POOR QUALSTY: 



The Antares IIA rocket motor, one of the Scout third stage propulsion units, 
is manufactured by Allegany Ballistics Laboratory (ABL) , Hercules Powder 
Company, Cumberland, Maryland. The motor case and nozzle are fabricated 
from reinforced plastics. The composite modified double base propel lant is 
a case-bonded slotted-cyl inder grain configuration. Ignition is accomplished 
by a dual squib rocket motor type igniter. 




30.05 



Total Impulse - Lb. - Sec. - Vacuum 

Specific Impulse - Lb. - Sec/Lb. - Vacuum 

Burning Time - Total - Sec. 

Thrust - Avg. Web - Lbs. - Vacuum 

Weight - Total - Lbs. (W^) 

Weight - Fuel - Lbs. (Wp) 

Mass Ratio - Wp/W^ 

Nozzle Expansion Ratio 

Weight Consumed - Lbs. 

Nozzle Exit Area - Ft.2 



724,673. 


281.40 


35.90 


20,931. 


2,812. 


2,575. 


0.91 


1-7 en 

1 M ,^J\J 


2,600. 


4.35 



Figure 4T.- Scout third stage. 



ANTARES I I lA MOTOR DATA 



66 orig^aa. t--;^": 

OF POOR Q'J'^- 



The Antares MIA rocket motor, an optional Scout third stage propulsion unit, 
is manufactured by Thiokol Corporation, Elkton, Maryland, The Antares 1 1 lA 
is an improved version of the Antares MA. The motor case and nozzle are 
fabricated from reinforced plastics. The HTPB propel lant is a case-bonded 
slotted-cyl inder grain configuration. Ignition is accomplished by a dual 
bridge pyrogen type igniter. 




30.37 in 



28.97 in. 



Total Impulse - Lb. - Sec. - Vacuum 

Specific Impulse - Lb. - Sec/lb. - Vacuum 

Burning Time - Total - Sec. 

Thrust - Avg. Web - Lbs. - Vacuum 

Weight - Total - Lbs. (W^) 

Weight -Fuel -Lbs. (Wp) 

Mass Ratio - Wp/Wt 

Nozzle Expansion Ratio 

Weight Consumed - Lbs. 

Nozzle Exit Area - Ft.2 



840,200. 

296.47 

46.0 

18,490. 

3,072. 

2,834. 

0.922 
42.83 
2,860. 
4.48 



14 



Figure 42.- Alternate Third Stage. 



ORIGINAL 



r^ 13 



OF POOR QUALITY 



67 



The Altair I lA rocket motor (X-258) , Scout System upper-stage propulsion unit, 
is manufactured by Allegany Ballistics Laboratory (ABL) , a U.S. Navy BuOrd 
facility operated by Hercules Powder Company, Cumberland, Maryland. Only three 
more Altair MA rocket motors will be used on Scout and then the Altair IMA 
will be used permanently. 




ALTAIR X258 





Altair 




X258-B1 


Total Impulse - Lb. - Sec. 
Vacuum 


139,294 


Specific Impulse - Lb. - Sec. /Lb. 
Vacuum 


278.1 


Burning Time - Total - Sec. 


24.0 


Thrust - Avg.- Web - Lbs. - Vac. 


6,176 


Weight - Total - Lbs. 


573 


Weight - Fuel - Lbs. 


500.8 


Mass Ratio - W /W 
P t 


.874 


Nozzle Expansion Ratio 


25.08 


Weight Consumed - Lbs. 


507.2 



Figure 43.- Scout-A fourth stage. 



68 



OF POOR QU/sLsr 



ALTAIR IIA - PERFORMANCE-VACUUM 



26' 
24 

22- 
20-- 



N 



2 18- 

X! 

O 14- 
< 12 






W 
ft 

s 

ft 



10-- 



8-- 



6-- 



2 

oi 








8 



16 20 24 28 32 36 



TIME - SEC. 



Figure ^k.- X-258 rocket motor data, 



OF POOR QUtd 



69 



FW-4S MOTOR DATA 



The Altair IlIA rocket motor (FW-4S) , Scout fourth-stage propulsion unit, is 
manufactured by United Technology Center (UTC) , Sunnyvale, California, a 
division of United Aircraft Corp. The motor case is filament wound of fiber- 
glass. The PBAN (polybutad iene acrylic acid - Acr i loni tr i le) composite pro- 
pel lant grain configuration is a case bonded circular perforation with one 
transverse slot. Ignition is accomplished by a dual squib rocket motor-type 
igniter. This motor replaced the Altair MA. 




Total Impulse - Lb. - Sec. - Vacuum 


172,243 


Specific Impulse - Lb. - Sec/Lbs. - Vacuum 


284.07 


Burning Time - Total - Sec. 


31.47 


Thrust - Avg. Web - Lbs. - Vacuum 


5,857 


Weight - Total - Lbs. (Wt) 


664.3 


Weight - Fuel - Lbs. (Wp) 


606.3 


Mass Ratio - Wp/Wt 


0.91 


Nozzle Expansion Ratio (Initial) 


52.8 


Weight Consumed - Lbs. 


611.3 


Nozzle Exit Area - Ft.2 


1.5 



Figure ^+5.- Scouts B thru G fourth-stage propulsion unit. 



70 



ALCYONE I A MOTOR DATA 



(a) 



ORiGU^IAL PAGE ?S 
OF POOR QUALITY 



The Alcyone I A rocket motor. Scout standard fifth stage propulsion unit is manufactured by the 
Hercules Powder Company, Magna, Utah. The motor case is filament wound of fiberglass. The 
modified double base propellant is a case bonded cylindrical perforation with longitudinal fins in the 
aft region. The igniter is a basket type containing BKNO3 pellets with dual initiators. 



% *, i< ~, ^^ 






' '$^.39 m 



^- ki , -r- 




■ ■;?,.. 






fit' 


■ 


d 


r\ 



81.84 CM 
(32.22 IN.)' 







Total Impulse - N-Sec. - Vacuum 

Specific Impulse - N-Sec./Kg - Vacuum 

Burning Time - Web — Sec. 

Thrust - Avg. Web - N-Vacuum 

Weight - Total - Kg (Wt) 

Weight - Fuel - Kg (Wp) 

Mass Ratio - Wp/W^ 

Nozzle Expansion Ratio 

Weight Consumed — Kg 

Nozzle Exit Area - M^ 



31.24 CM 
(12.30 IN.) 



'\ n 



236,013. 
2,710.3 
8.42 
27,491. 
98.2 
87.1 
0.887 
18.6 
88.2 
0.075 



Figure kS.- Scout fifth-stage propulsion unit. 
(^)Figure k7 shows the Alcyone in the fifth-stage pay load envelope. 



ORlGfS^AL PAGE 53 
OF POOR QUALITY 

PAYLOAD INTERFACE 



71 



STA^ 
:5.00> 



LIMITS OF PAYLOAD 
UMBILICAL DOOR 
LOCATION 



^STA^ 

VI 4.23; 



PAYLOAD EXTENDED 
INTO THIS AREA REQUIRES 
DETAILED COORDINATION 




^TAN 
[AO.OO) 



^TAN 
V26.0C 



"^TAN 

rio.sq/ 



PAYLOAD 

SEPARATION 

PLANE 





q."F" SECTION 

UMBILICALS /'STA^ 

29.657 



FIFTH STAGE 
SEPARATION PLANE 




^STA> 
U7.77/ 

"It^ 



4046' 



FOURTH STAGE 
MOTOR (FW-4S) 



MOTOR BUMPER ^^-^y 



"D" 
SECTION 



FOURTH STAGE 
S EPARATION PLANE / ^STA> 
~ I99.70; 



Figure k7.- FIVE-STAGE SCOUT PAYLOAD ENVELOPE 



72 
TABLE XVI - AEROJET MOTOR HISTORY, 
ALGOLS I AND II 



ORIGINAL PA2^ 
OF POOR 



Number 


Contract 






Use 




IA-1 


NAS5- 


-53 






Test 




IA-2 


NAS5- 


-53 






Test 




IA-3 


NAS5 


-53 






STX 




'•-IA-4 


NAS5 


-53 




St 


orage-W 




IB-5 


NAS5 


-53 






Test 




IB-6 


NAS5 


-53 






ST-1 




IB-7 


NAS5 


-53 






ST-3 




IB-8 


NAS5 


-53 


Reject 


-Navy (Hydro) 




IB-9 


NAS5 


-53 






ST-2 




IB-10 


NAS5 


-53 






ST-5 




IC-11 


NAS5 


-53 






ST-6 




IC-12 


NAS5 


-53 


Test (C 


:ase S-144) 




IC-13 


NASI 


-585 






Test 




IC-14 


NASI 


-585 


At 


r 


Force D-3 




IC-15 


NASI 


-585 


Ai 


r 


Force D-4 




IC-16 


NASI 


-585 






Reject 




IC-17 


NASI 


-585 






Reject 




IC-18 


NASI 


-585 


Ai 


r 


Force D-5 




IC-19 


NASI 


-585 


Ai 


r 


Force D-6 




IC-20 


NASI 


-585 


Ai 


r 


Force D-8 




IC-21 


NASI 


-585 


Rej 


ect (Rep 1/25) 




-VIC -22 


NASI 


-585 




St 


orage-W 




IC-23 


NASI 


-585 






ST-4 




\C-2k 


NASI 


-585 






ST-7 




IC-25 


NASI 


-585-3 


Ai 


r 


Force D-7 




IC-26 


NASI 


-1330 






ST-8 




IC-27 


NASI 


-1330 






ST-9 




ID-28 


NASI 


-1330 






Test 




ID-29 


NASI 


-1330 






S-111 




ID-30 


NASI 


-1330 






MSC 




ID-31 


NASI 


-1330 






MSC 




ID-32 


NASI 


-1330 






MSC 




^V|D-33 


NASI 


-1330 






S-132 




ID-34 


NASI 


-1330 






MSC 




ID-AF-1 


Air 


Force 






S-112 




ID-AF-2 


Air 


-orce 






S-117 




ID-AF-3 


Air 


■orce 






S-121 




*ID-AF-it 


Air 


-orce 






MSC 




IIA-1 


NASI 


-1330 






Test 




IIA-2 


NASI 


-1330 






Test 




1 IA-2R 


NASI 


-1330 






Test 




1 IA-3 


NASI 


-1330 






Test 




1 IA-3R 


NASI 


-1330 






Test 




IIA-i+ 


NASI 


-1330 






S-118 




1 IA-5 


NASI 


-1330 






S-114 




IIA-6 


NASI 


-1330 






S-115 




1 IA-7 


NASI 


-1330 






S-119 




1 IA-8 


NASI 


-1330 






5-116 




VrA-l iA-9 


NASI 


-1330 






S-126 





-"Traded with 
--'w'cSold to Air 
MSC-transfer 



Air Force (lA-4 AF propert 
Force (63-27) 
red to MSC. 



y). 



Number 


Contract 


Use 


IIA-IO 


NASI -1330 


Test 


IIA-11 


NASI -1330 


Test 


IIA-12 


NASI -1330 


S-120 


IIA-13 


NASI -1330 


S-113 


IIA-|i+ 


NASI -1 330- 


S-llO 


IIB-15 


NASl-1330- 


Test 


IIA-16 


NASI-1330- 


S-127 


IIA-17 


NASI-1330- 


Test -HC (Case, LRC) 


IIA-18 


NASl-1330- 


Test 


IIA-19 


NASl-1330- 


Test 


IIA-20 


NASI-1330- 


Assgnd, SRT-HC 


IIA-21 


NASl-1330- 


S-122 


1 IA-22 


NASI-1330- 


S-128 


1 IA-23 


NASl-1330- 


Storage 


IIA-2i* 


NASI-1330- 


S-125 


IIB-25 


NASl-1330- 


S-134 


IIB-26 


NASl-1330- 


S-124 


IIB-27 


NAS1-1330-J 


3 S-129 


IIB-28 


NASl-1330-i 


3 S-136 


IIB-29 


NASI-1330-! 


3 S-I23 


IIB-30 


NASI -1 330- 


14 S-130 


IIB-31 


NAS 1 -3833 tR-66551) Test 


IIB-32 


NASI -3833 


S-133 


IIB-33 


NASI -3833 


S-135 


IIB-34 


NASI -3833 


S-137 


IIB-35 


NASI -3833 


S-138 


IIB-36 


NASI -3833 


S-131 


IIB-37 


NASI -3833 


S-139 


IIB-38 


NASI -3833 


S-140 


IIB-39 


NASI -3833 


S-148 


IIB-40 


NASI -3833 


S-141 


IIB-41 


NASI -3833 


S-143 


IIB-42 


NASI -3833 


S-151 


IIB-43 


NASI -3833 


S-145 


IIB-¥f 


NASI -3833 


S-142 


IIB-it5 


NASI -3833 


S-146 


IIB-i+6 


NASI -3833 


S-153 


IIB-47 


NASI -3833 


S-150 


1 1 B-48 


NASI -3833 


S-149 


IIB-49 


NASI -3833 


S-152 


IIB-50 


NASI -3833 


S-147 


IIB-51 


NASI -3833 


S-154 


MB-52 


NASI -3833 


S-155 


IIB-53 


NASI -3833 


S-157 


llB-54 


NASI -3833 


S-159 


IIB-55 


NASI -3833 


Static Tests 


IIB-56 


NASI -3833 


S-156 


MB-57 


NASI -3833 


S-158 


IIB-58 


NASI -3833 


S-162 



ORFGIWAL 

OF POOR QUALITY 






73 



TABLE XVI Concluded - AEROJET MOTOR HISTORY. 



ALGOLS I AND II 



Number 

IIB-59 
I 18-60 

I 18-61 
I 18-62 
I 18-63 
118-64 
1 18-65 
I 18-66 

IIB-67 
118-68 
1 18-69 
1 1 8- 70 
118-71 
I 18-72 
118-73 
I 18-74 
118-75 



Contract 

NASI -5610 
NASI -5610 
NASI -5610 
NAS1-5610 
NASI -5610 
NASI -5610 
NASI -5610 
NASI -5610 
NASI -5610 
NASI -5610 
NASI -5610 
NASI -5610 
NAS1-5610 
NAS1-5610 
NASI -5610 
NASI -5610 
NASI-56IO 



Use 

S-161 
S-168 
Test 

S-160 
S-172 
S-I67 
S-164 
S-175 
S-I69 

s-n't 

S-I63 
Storage-Sh.Lf 
S-166 
S-171 
S-I65 
S-173 
S-176 



Stdy. 



Number 

I 1 8- 76 
IIC-77 

lie- 78 

I IC-79 
IIC-80 
IIC-81 
I IC-82 
IIC-83 
1 1 C-84 
I IC-85 
I IC-86 
IIC-87 
IIC-88 
I IC-89 
I IC-90 
IIC-91 
I IC-92 
ilC-93 



Contract 



NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 



-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 
-7199 



Use 

S-177 
S-lMf 
S-I80 
S-I87 
Unassigned 
Unass igned 
Unassigned 

S-179 
S-182 
Reject 
S-178 
Unass igned 
Unassigned 

S-I83 
Unass igned 
Unassigned 
Unass igned 
Unass igned 



Number 



5502-1 
5502-1 
5502-1 
5502-1 
5502-1 
5502-1 
5502-1 
5502- I 
5502-1 
5502-1 
5502-1 
5502-1 
5502-1 
5502-1 
5502-1 

jj\j-t- 1 

5504- I 
5504- I 



-1 
■2 
-3 
-4 
■5 
-6 

-7 
-8 

-9 

-10 

-11 

-12 

-13 

-15 

-16 



■2P18 
-3P19 



TA8LE XV I I 



Contract 



NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 



■9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 
-9258 



-1 pi -7 MAci _i 7 1 nn 



NASI' 
NASI' 



13100 
13100 



UNITED TECHNOLOGY MOTOR HISTORY, ALGOL III 
Use Number Contract 



Use 



S-170 


5504- 1 


I-4P20 


NAS1- 


13100 


S-201 


S-184 


5504- 1 


I-5P21 


NAS1- 


13100 


S-192 


S-181 


5504- 1 


I-6P22 


NAS1- 


13100 


S-202 


S-185 


5504- 1 


I-7P23 


NAS1- 


13100 


S-203 


Test 


5504- 1 


I-8P24 


NAS1- 


13100-13 


Assigned S-1 


S-190 


5504- 1 


I-9P25 


NAS1- 


13100-13 


Unassigned 


S-188 


5504- i 


I-10P26 


NAS1- 


13100-13 


Unass igned 


S-191 


5504- 1 


I-11P27 


NAS1- 


13100-13 


Unass igned 


S-186 


5504- 1 


I-12P28 


NAS1- 


13100-13 


Unassigned 


S-189 


5505-1 


1-1 


NAS1- 


14200-10 


Unassigned 


S-194 


5505-1 


i-2 


NAS1- 


14200-10 


Unass igned 


S-195 


5505-1 


1-3 


NAS1- 


14200-10 


Unass igned 


S-196 


5505- 1 


1-4 


NAS1- 


14200-10 


Unassigned 


S-193 


5505-1 


1-5 


NAS1- 


14200-10 


Unass igned 


S-197 


5505-1 


1-6 


NAS1- 


14200-10 


Unassigned 


S-200 


5505-1 


1-7 


NAS1- 


14200-10 


Unass igned 


S-198 


5505-1 


i-8 


NAS1- 


14200-10 


Unass igned 


Test 


5505-1 


1-9 


NASl- 


14200-10 


Unass igned 




5505-1 


1-10 


NAS1- 


14200-10 


Unass igned 



7^ 
TABLE XVIII - THIOKOL MOTOR HISTORY, CASTOR I 



OF POOR QlJALrri' 



Castor I (XM-33) 



Number 


Contract 


Use 


Number 


Contract 


Use 


IE5-62 


L-55931-3 


Test 


IE5-176 


AF Contract 


S-117 


IE5-77 


L-55931-3 


ST-1 


IE5-177 


AF Contract 


S-121 


IE5-82 


L-55931-3 


ST-2 


^v.viE5-178 


AF Contract 


S-I38 


IE5-83 


L-55931-3 


ST-3 


IE5-179 


L-206I 


S-133 


IE5-92 


L-55931-3 


ST-k 


IE5-180 


L-2061 


S-128 


IE5-93 


L-55931-3 


Test 


IE5-181 


L-2061 


5-116 


IE5-9^ 


L-55931-3 


Air Force 


IE5-182 


L-206I 


5-125 


iE5-95 


L-55931-3 


Air Force 


IE5-183 


L-2061 


5-127 


IE5-102 


L-77203-5 


Air Force 


IE5-184A 


L-2061 


5-123 


IE5-103 


L-77203-5 


Air Force 


IE5-185A 


L-2061 


S-136 


IE5-10if 


L-77203-5 


Air Force 


IE5-186 


L-2061 


Reject 


IE5-107 


L-77203 


Air Force 


IE5-187 


L-2061 


Reject 


>IE5-108 


L-77203 


ST-6 


IE5-188 


L-2061 


S-134 


1E5-109 


L-77203 


Air Force 


IE5-189 


L-2061 


5-139 


IE5-110 


L-77203 


Test 


IE5-190 


L-2061 


5-141 


IE5-in 


L-77203 


Air Force 


IE7-191 


L-2061 


AF B.S.J. 


IE5-112 


L-77203 


Air Force 


IE7-192 


L-2061 


AF B.S.J. 


IE5-113 


L-77203 


Air Force 


IE7-193 


L-2061 


AF B.S.J. 


IE5-11^ 


L-77203-5 


Reject 


IE7-194 


L-2061 


Reject 


IE5-124 


L -89845 


ST-7 


IE7-195 


L-2061 


AF Beanstalk 


IE5-125 


L- 898^*5 


ST-8 


IE7-196 


L-2061 


AF Beanstalk 


IE5-126 


L-89845 


Reject 


IE7-197 


L-2061 


AF Beanstalk 


-1E5-128 


L-67666 


ST-9 


IE7-198 


L-2061 


AF Beanstalk 


IE5-143 


L-77203-6 


S-113 


IE7-199 


L-2061 


AF Beanstalk 


IE5-1^7 


L-93419 


S-111 


IE5-252 


L-93^19-8 


5-124 


IE5-1^8 


L-93419 


S-120 


IE7-253 


L-6992 


AF B.5.J. 


IE5-149 


L-93419 


S-114 


IE7-254 


L-6992 


AF B.S.J. 


IE5-150 


L-93419 


S-118 


IE7-255 


L-6992 


AF B.S.J. 


VIE5-151 


L-93419 


Air Force 


IE7-257 


L-6992-2 


AF B.S.J. 


IE5-152 


L-93419 


S-122 


IE7-258 


L-6992-2 


AF B.S.J. 


IE5-153 


L-93'+19 


S-115 


IE7-259 


L-6992-2 


AF B.5.J. 


IE5-15^ 


L-93419 


S-119 


IE7-260 


L-6992-2 


AF B.S.J. 


IE5-155 


L-93419 


S-110 


IE7-261 


L-6992-2 


AF B.S.J. 


IE5-156 


L-93419 


Test 


IE7-262 


L-6992-2 


AF B.S.J. 


''^IE5-157 


L-93419 


Exch. for IE5-128 


IE7-303 


L-2061 -8 


AF B.S.J. 


VIE5-158 


L-93419 


S-126 


IE5-326 


L-77203 


5T-5 


iE5-159 


L-93419 


S-129 


IE5-371 


Unknown 


(Case 5-144) 


IE5-160 


L-93419 


S-132 


IE5-422 


L-2061 -9 


S-130 


IE5-161 


L-93419 


S-137 


IE5-423 


L-2061 -9 


S-135 


IE5-175 


AF Contract 


5-112 


IE5-534 


NASI -5034 


Storage 








IE5-535 


NASI -5034 


Storage 



'-VI28 borrowed from LRC, returned #157. 
""Lent AF, reed. #178 in return. 
■/w'w'.-Bor rowed 1 08 from 609A Program, replaced by 151. 



ORIGINAL PAGSjS 
OF POOR QUALITY. 



75 





TABLE XIX - 


THIOKOL MOTOR HISTORY, CASTOR 


II (TX354-3) 




Number 


Contract 


Use I 


■dumber 


Contract 


Use 


IIA-1 


LI 5993 


Test 


IA-185 


NASI -71 99 


S-144 


1 IA-2 


LI 5993 


Reject 


IA-186 


NASI -71 99 


S-180 


IIA-3 


LI 5993 


Test 


IA-I87 


NASI -71 99 


S-184 


IIA-U 


LI 5993 


Test 


IA-188 


NASI -71 99 


S-I85 


IIA-5 


LI 5993 


Test 


IA-I89 


NASI -71 99 


S-I87 


IIA-6 


LI 5993 


Test 


IA-190 


NASI -7199 


S-190 


II A- 7 


LI 5993 


Test 


IA-191 


NASI -71 99 


S-181 


IIA-16 


NASI -5034 


S-143 


IA-192 


NASI -71 99 


S-I83 


IIA-1 7 


NASI -5034 


S-142 


lA-193 


NASI -71 99 


S-179 


IIA-18 


NASI -5034 


S-146 


IA-194 


NASI -7199 


S-178 


IIA-19 


NASI -5034 


S-147 


IA-195 


NASI -71 99 


S-170 


1 IA-20 


NASI -5034 


S-145 


IA-196 


NASI -71 99 


S-197 


1 IA-21 


NASI -5034 


S-148 


IA-197 


NASI -7199 


S-I82 


1 IA-22 


LI 5993 


Test 


IA-198 


NASI -71 99 


S-188 


1 IA-23 


NASI -5034 


S-131 


IA-199 


NASI-7I99 


S-191 


1 IA-2if 


NASI -5034 


S-140 


IA-200 


NASI -71 99 


S-186 


1 IA-25 


NASI -5034 


S-149 


IA-201 


NASI -71 99 


S-I89 


1 IA-26 


NASI -5034 


S-152 


IA-325 


Sandia 


Test Reject 


MA-27 


NASI -5034 


S-150 


IA-326 


Sandia 


Shelf Life 


1 IA-28 


NASI -5034 


S-153 


IA-328 


Sandia 


Shelf Life 


1 IA-29 


NASI -5034 


S-151 


IA-382 


NASI -11400 


S-195 


1 IA-96 


NASI -5883 


S-157 


IA-383 


NASI -11 400 


S-196 


1 IA-97 


NASI -5883 


S-160 


IA-384 


Sandia-Ret'd 


S-202 


1 IA-98 


NASI -5883 


S-154 


IA-385 


Sandia-Ret'd 


S-192 


1 IA-99 


NASI -5883 


Test (Case to 1 


JKC Show) 






IIA-1 00 


NASI -5883 


S-155 


IA-386 


Sandia-Ret'd 


Unassigned 


IIA-101 


NASI -5883 


S-159 


IA-387 


Sandia-Ret'd 


S-203 


IIA-1 02 


NASI -5883 


S-156 


IA-390 


NASI -11400 


S-194 


IIA-1 03 


NASI -5883 


S-161 


IA-391 


NAS1-11400 


S-192 


II A- 104 


NASI -5883 


S-168 


IA-392 


NAS1-11400 


S-193 


IIA-105 


NASI -5883 


S-158 


IA-393 


NASI -11400 


S-200 


IIA-1 70 


NASI -5610 


S-162 


IA-394 


NASI -11400 


S-198 


IIA-1 71 


NASI -5610 


S-169 


IA-395 


NASI -11 400 


S-201 


IIA-1 72 


NASI -5610 


S-I65 


IA-808 


NASI -14200-6 


Unassigned 


IIA-1 73 


NASI -561 


S-I67 


IA-809 


NASI -14200-6 


Unassigned 


IIA-1 74 


NASl-5610 


S-145 


IA-810 


NASI -14200-6 


Assigned S-199 


IIA-1 75 


NASI -5610 


S-174 


IA-811 


NASI -14200-6 


Unass igned 


IIA-1 76 


NASI -5610 


S-171 


IA-812 


NASI -14200-6 


Unassigned 


IIA-1 77 


NASI -561 


Test 


IA-8I3 


NASI -14200-6 


Unassigned 


IIA-1 78 


NASI -5610 


S-I63 


IA-814 


NASI -14200-6 


Unassigned 


IIA-1 79 


NASI-56IO 


S-172 


IA-8I5 


NASI -14200-6 


Unass igned 


IIA-180 


NASI-56IO 


S-1/5 


IA-S16 


NASI -14200-6 


Unass igned 


IIA-181 


NASI-56IO 


S-177 


IA-8I7 


NASI -14200-6 


Unassigned 


llA-182 


NASI -5610 


S-173 


IA-818 


NASI -14200-14 


Unass igned 


IIA-I83 


NASI -5610 


S-166 


IA-8I9 


NASI -14200-14 


Unass igned 


IIA-1 84 


NASI -5610 


S-176 


IA-820 


NASI -14200-14 


Unassigned 








lA-821 


NASI -14200-1 4 


Unass igned 



ORIGINAL PAt2S [^ 
OF POOR QUMJTi 



76 



TABLE XX - HERCULES MOTOR HISTORY, ANTARES MA. 



Number 


Contract 




Use 




Al-1 


NOrd 16640(3- 


-138)>v.v 


Test 




Al-2 


NOrd 16640(3- 


-138)'W> 


Test 




Al-3 


NOrd 16640(3- 


-138) — 


Test 




A1-^ 


NOrd 16640(3- 


-138)'V.v 


Test 




Al-5 


NOrd 16640(3- 


-138) -w- 


Test 




Al-6 


NOrd 16640(3- 


■138)'Wf 


Test 




Al-7 


NOrd 16640(3- 


-138)Vn!: 


Test 




Al-9 


NOrd 16640(3- 


■138)VwV 


Test 




Al-11 


NOrd 16640(3- 


.138)vv,v 


Test 




A3-16 


L-93985 




s-ni 




A3-17 


L-93985 




ST-9 




A2-18 


NOrd 16640(3- 


•138)'V-v 


Test 




A2-19 


NOrd 16640(3- 


-138)^'"'r 


Test 




A2-20 


NOrd 16640(3- 


-138)-w- 


Test 




A2-21 


NOrd 16640(3- 


-138)v:,v 


Test 




A2-22 


NOrd 16640(3- 


■ l38)-'^v 


Test 




A2-23 


NOrd 16640(3- 


-138)''ov 


Test 




A3-2i+ 


L-93985 




S-117 




A3 -25 


L-93985 




S-112 




A3 -26a 


L-93985 




S-121 




A2-100 


L-93985 




USNAP-Crane Test 




A2-101 


L-93985 




Test 




A2-102 


L-3920 




Test 




A2-103A 


L-93985 




Test 




A3- 104 


L-3920 




Reject 




A3-105 


L-93985 




S-114 




A3-106 


L-3920 




S-116 




A2-107A 


L-93985 




Test-fire 




A3-108 


L-93985 




S-118 




A3-109C 


L-3920 




S-127 




A3-110A 


L-93985-3 




S-llO 




A2-111 


L-93985 




Test 




A3-112 


L-93985-3 




S-126 




A2-113 


L-3920 




Test 




A2-114 


L-3920 




Test 




A2-115 


L-3920 




Test 




A2-116 


L-3920 




Burst Test 




A3-117 


L-3920 




S-119 




A4-I18 


L-3920 




S-132 




A4-119 


L-3920 




S-II5 




A3-120 


L-3920 




Reject-Test 


V; 


A3-122 


L-3920 




S-120 




A4-123 


L-3920 




Ai r Force 




A3- 124 


L-3920 




Air Force (ETR) 




A2-126A 


L-3920 




Test - SRT 




A2-127 


L-3920-9 




Test 




A2-128 


L-3920 




S-113 




A3-129 


L-3920 


Reject -AMPD 




A3-130 


L-3920 




S-124 




A3-132 


L-3920-2 




S-128 


«t 


A4-133 


L-3920 


A! r Force 
'd to Scout. 




*Wasp motor transferre 




**Direct 


by OSSA-Hqs. 









Number 


Contract 


A3- 


134 


L-3920 


A3- 


135 


L-3920 


A3- 


I36A 


L-3920 


A2- 


137 


NASI -3493 


A3- 


139 


L-3920 


A3- 


140 


L-3920 


A3- 


141 


L-3920 


A2- 


142 


L-3920 


A3- 


43 


L-3920 


A5- 


144 


L-3920 


A3- 


45 


L-3920-4 


A3- 


46 


L-3920-4 


A3- 


48 


L-3920 


A2- 


50 


L-3920-4 


A3- 


51 


L-93985-12 


A3- 


52 


L-3920 


A3- 


53 


L-3920 


A3- 


54 


L-3920 


A3- 


55 


L-3920 


A3- 


56 


L-3920 


A3- 


57 


L-3920 


A5- 


58 


L-93985-12 


A3- 


59 


NASI -3493 


A3- 


60 


NASI -3493 


A3- 


61 


NASI -3493 


A3- 


62 


NASI -3493 


A3- 


63 


NASI -3493 


A3- 


64 


NASI -3493 


A3- 


65 


NASI -3493 


A3- 


66 


NASI -3493 


A3- 


67 


NASI -3493 


A3-1 


68 


NASI -3493 


A3-1 


69 


NASI -3493 


A3-1 


70 


NASI -3493 


A3-1 


71 


NASI -3493 


A3-1 


72 


NASI -3493 


A3- 


73 


NAS 1 -3493 


A3- 


74 


NASI -3493 


A6- 


75 


NAS 1-3493 


A6- 


76 


NAS 1-3493 


''-A3- 


77 


NAS 1-3493 


A3- 


78 


NAS 1-3493 


A2- 


79 


NAS 1-3493 


A3- 


80 


NAS 1-3493 


A3- 


81 


NAS 1 -3493 


A3- 


82 


NAS 1-3493 


A3- 


83 


NAS 1 -3493 


A3- 


84 


NAS 1-3493 


A2- 


85 


NAS 1-3493 


>VA3- 


86A 


NAS 1-3493 



Use 



S-122 
Air Force (ETR) 
S-129 
Q..A. Test 

S-133 

Air Force 

Air Force 
H-Assigned Test 

S-123 

Fi re 

S-134 

S-125 

Reject -Navy 
ABL-Nozzle Test 

S-152 

Air Force 

Air Force 

S-138 

Air Force 

Air Force 

S-130 

Fire 

S-135 

S-131 

S-147 

Reject -case 

S-154 

S-146 

S-139 

S-136 

S-137 

Demol ished 

S-142 

S-143 
Q.A. Test (S-144 case) 

S-141 

S-140 

S-145 

Air Force (WS) 

Air Force (WS) 

S-149 

QA5883 

Wasp (SPARTA) 

Ai r Force 

S-150 

S-153 

S-148 

S-151 

Wasp 

Reject-Storage 



ORIGINAL PAGE IB 
OF POOR QUALITY 



77 



TABLE XXI - THIOKOL MOTOR HISTORY 







ANTARES 


IIA 






Number 


Contract 


Use 


Number 


Contract 


Use 


'VA3-187 


NASI -3493 


Case Test-SRT 


B3-301 


NASI -71 99 


S-166 


5VA3-201 


NASI -3493/5883 


S-156 


83-302 


NASI -71 99 


S-183 


>'-A3-202 


NASI -3493/5883 


S-155 


83-303 


NASI -7199 


S-184 


'•-A3-203 


NASI -3493/5883 


Test-AEDC# 


83-304 


NASI-7199 


S-170 


A3-204 


NASI -5883 


Reject^'-'- (W.I.) 


83-305 


NASI-7199 


S-I63 


B3-205 


NASI -5883 


S-159 


83-306 


NASI-7199 


S-190 


83-206 


NASI -5883 


S-160 


B3-307 


NASI-7199 


S-I87 


B3-207 


NASI -5883 


S-161 


83-308 


NASI-7199. 


S-188 


B3-208 


NASI -5883 


(Test)Grain Mis- 
oriented 


83-309 


NASI-7199 


S-195 


B3-209 


NASI -5883 


S-164 


B3-310 


NASI-7199 


S-178 


B3-210 


NASI -5883 


S-168 


83-311 


NASI-7199 


S-I82 


B3-211 


NASI -5883/5610 


Dropped - Reject 


83-312 


NASI-7199 


S-185 


B3-212 


NASI -5883/5610 


S-158 


83-313 


NASI-7199 


S-I8I 


B3-213 


NASI -5610 


S-I62 


B3-314 


NASI-7199 


S-180 


83-214 


1^ NASI -5610 


S-172 


83-315 


NASI-7199 


S-186 


83-215 


NASI -561 


S-I65 


83-316 


NASI-7199 


S-I89 


83-216 


NASI -561 


S-I67 


83- 


NASI -5883 


Replaced 83-208 


B3-217 


NASI-56IO 


S-I69 


84-402 


NASl-11400 


S-179 


B3-218 


NASI -561 


S-174 


B4-404 


NASI -11400 


S-197 


83-219 


NASI -5610 


S-176 


84-405 


NASl-11400 


S-193 


83-220 


NASI -561 


S-157 


84-408 


NASl-11400 


S-200 


83-221 


NASI -5610 


S-171 


84-409 


NASl-11400 


S-198 


83-222 


NASI -561 


Assigned Test-S.L. 


B4-41 


NAS1-14200 


Unass igned 


83-223 


NASI -5610 


S-177 


84-41 1 


NASI -14200 


S-201 


83-224 


NASI -5610 


S-173 


84-41 2 


NASI -14200 


S-202 


83-225 


NASI -5610 


S-144 


84-41 3 


NASl-14200 


Unass igned 


83-226 


NASI-56IO 


S-175 


84-414 


NASI -14200 


Unass igned 








84-41 5 


NASl-14200 


Assigned S-199 



ANTARES I I 8 



Number 



Contract 



Use 



84-401 


NASl-11400 




S-191 


84-403 


NASl-11400 




AEDC Test 


84-406 


NASl-11400 




S-196 


84-407 


NASl-11400 




S-194 


B4-416 


NASl-11400 


Destroyed in Hydrotest 


84-41 7 


NASI -11400 


H 


E. Test 


84-418 


NASI -11400 


H 


E. Test 



TABLE XXII - ANTARES I IIA 



Number 


Contract 
NAS1-15100-R44 


Use 
Test 




Number 
E-5 


Contract 
NASl-14200-5 


Use 


D-1 


Unass igned 


D-2 


NASI-I510O-R44 


Test 




E-6 


NASl-14200-5 


Unass iqned 


D-3 


NAS1-15100-R44 


Test 




E-7 


NASl-14200-5 


Unass igned 


Q-1 


NAS1-15100-R44 


Test 




E-8 


NASl-14200-5 


Unass igned 


Q-2 


NAS1-15100-R44 


Test 




E-9 


NASl-14200-5 


Unass igned 


Q-3 


NAS1-15100-R44 


Test 




E-10 


NASl-14200-5 


Unass igned 


E-1 


NAS1-15100-R44 


S-203 




E-11 


NASl-14200-5 


Unass igned 


E-2 


NAS1-14200-5 


S-192 




E-12 


NASl-14200-5 


Unass igned 


E-3 


NAS1-14200-5 


Unass! 


gned 


E-13 


NASl-14200-5 


Unass igned 


E-4 


NASl-14200-5 


Unassi 


gned 


E-14 


NASl-14200-5 


Unass igned 



>'-HPC. 



#Case to LRC Show. 



''~'<Rep la cement due. 



78 
TABLE XXin(a) ' HERCULES MOTOR HISTORY, ALTAIR II 
Altair II (RH-X-258) History 



OF POOR Ql AL'A' 



Number 


Contract 
NASA Hq. 


Use 
Test 


Number 
'■<*C2-73-D 


Contract 


Use 


AI-1 


NASI -3698 


S-133 


Al-2 


NASA 


Hq. 


Test 


C2-74 


NASI -3698 


S-I35 


Al-3 


NASA 


Hq. 


Test 


CI -75 


NASI -3698 


S-137 


M-k 


NASA 


Hq. 


Test 


C2-76 


NASI -3698 


Air Force 


Al-5 


NASA 


Hq. 


Test 


C2-77 


NASI -3698 


Delta 


AI-6 


NASA 


Hq. 


Test 


C4-78 


NASI -3698-3 


Delta 


Al-7 


NASA 


Hq. 


Test 


C4-79 


NASI -3698-3 


Delta 


Al-9 


NASA 


Hq. 


Test 


C4-80 


NASI -3698-3 


Delta 


Al-10 


NASA 


Hq. 


Test 


*C3-8l-D 


NASI -3698-3 


S-136 


Al-13 


NASA 


Hq. 


Test 


C4-82 


NASI -3698-6 


Aging test -1 968 


Al-15 


NASA 


Hq. 


Test 


C4-83 


NASI -3698-6 


Delta 


A2-18 


NASA 


Hq. 


Test 


C4-84 


NASI -3698-6 


Delta 


Al-19 


NASA 


Hq. 


Test 


C4-85 


NASI -3698-6 


Air Force 


A2-20 


NASA 


Hq. 


Test 


C2-86 


NASI -3698-3 


Delta 


A2-21 


NASA 


Hq. 


Test 


C4-87 


NASI -3698-6 


Delta 


A2-22 


NASA 


Hq. 


Test 


C4-88 


NASI -3698-9 


Delta 


Bl-23 


NASA 


Hq. 


Test 


C4-89 


NASI -3698-9 


Delta 


B]-2k 


NASA 


Hq. 


Test 


C4-90 


NASI -3698-9 


Delta 


81-25 


NASA 


Hq. 


Test 


C4-91 


NASI -3698-9 


Delta 


Bl-28 


NASA 


Hq. 


Test 


C4-92 


NASI -3698-9 


Delta 


Bl-30 


NASA 


Hq. 


Test 


E2-100 


NASI -3698 


Test 


Bl-32 


L-8735 


Test 


E4-101 


NASI -3698 


Reject -case 


81-3^ 


L-8735 


Test 


E4-102 


NASI -3698 


Reject -case 


81-35 


L-6990 


Test 


E4-103 


NASI -3698 


Reject-case 


81-36 


L-6990 


Test 


E4-104 


NASI -3698 


Empty case 


81-37 


L-6990 


Test 


E4-105 


NASI -3698 


Test 


Bl-39 


L-8735 


Test 


E4-106 


NASI -3698 


Test 


Bl-i+O 


L-8735 


Test 


E4-107 


NASI -3698 


Reject-Ins. 


81 -ill 


L-8735 


Test 


E10-108 


NASI -3698 


Test 


81-tf2 


L-8735 


Test 


E4-109 


NASI -3698 


Air Force 


b]-k5 


L-6990 


Test 


E8-110 


NASI -3698 


S-146 


81-46 


L-6990-2 


Test 


E4-111 


NASI -3698 


Reject-test 


Bl-47 


L-6990-4 


Test 


E4-112 


NASI -3698 


Reject -case 


81-48 


L-6990-3 


S-113 


ElO-113 


NASI -3698 


Air Force 


81-49 


L-6990-3 


Test 


E4-114 


NASI -3698 


Reject- Ins. 


81-50 


L-6990 


Test 


E4-115 


NASI -3698 


Mock-up 


81-53 


L-6990-4 


S-132 


E6-116 


NASI -3698 


S-142 


81-54 


L-6990-3 


Reject 


E6-117 


NASI -3698 


S-I41 


C1-55-L 


NASI 


-3664 


S-125 


E6-1I8 


NASI -3698 


S-143 


C1-56-D 


NASI 


-3664 


Test 


E6-119 


NASI -3698 


Air Force-Sata r 


C2-58-L 


NASI 


-3664 


Delta-test 


E6-120 


NASI -3698 


Reject -case 


>V82-60 


L-6990-5 


Delta-IMP 


E4-121 


NASI -3698 


Delta 


81-61 


L-6990-5 


S-122 


E6-122 


NASI -3698 


Test-case 


-''>X2-63-J 


NASI 


-3664 


Delta-test 


E6-123 


NASI -3698 


Test 


C1-64-N 


NASI 


-3664 


S-124 


E6-124 


NASI -3698 


Test 


C1-65-N 


NASI 


-3664 


Javel in 


E6-125 


NASI -3698 


S-138 


C1-66-N 


NASI 


-3664 


S-128 


E6-126 


NASI -3698 


S-139 


B2-67-D 


NASI 


-3664 


Delta 


E6-127 


NASI -3698 


Test 


CI -68 


NASI 


-3698 


S-134 


E6-128 


NASI -3698 


Test 


C2-69 


NASI- 


-3698 


Delta 


E6-129 


NASI -3698 


S-140 


CI -70 


NASI 


-3698 


S-129 


E6-130 


NASI -3698 


Test-Shelf Lif« 


C2-71 


NASI 


-3698 


Delta-test 


E6-131 


NASI -3698 


Air Force-Sat ar 


CI -72 


NASI 


-3698 


S-123 


V0V5VE6-I32 
vrfoWcE6-133 


NASI -3698 
NASI -3698 


Air Force-Satar 
Delta-Air Force 



'cOn loan to Delta, reed. 81 in return, 
'V*On loan to Delta, reed. 73 in return, 
*5WfDelta on loan to Air Force. 
*^Hr*Traded Air Force for FW-4S 20033- 



79 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLE XXI H (a) Concluded - HERCULES INCORPORATED. 

Altair I I (X-258) History 



NUMBER 



CONTRACT 



USE 



RHEe-IB'^ 


NAS 1-3698 


S-15^ 


RHE6-135 


NASI -3698 


S-157 


RHE6-136 


NAS 1-3698 


S-149 


RHE6-I37 


NAS 1-3698 


Air Force-Satar 


E6-I38 


NAS 1-5883 


Air Force-Satar 


E6-I39 


NAS 1-5883 


S-156 


E6-140 


NAS 1 -5883 


Delta-18 


E6-141 


NAS 1 -5883 


Delta-19 


E6-li+2 


NAS 1-5883 


Reject (Repl. w/l6l) Igniter Test 


E6-143 


NAS 1-5883 


S-155 


E5-1^4 


NAS 1-5883-3 


Reject 


E5-1^5 


NAS 1-5883 -3 


S-162 


E5-1^6 


NAS 1-5883 -3 


Rejected 


E5-1^7 


NASI -5883-3 


Shelf Life Test 


E5-1^8 


NASI -5883-3 


Inventory 


E5-1^9 


NASI -5883-3 


S-176 


E5-150 


NASI -5883-3 


S-178 


E5-151 


NASI -5883-3 


Canceled 


E5-152 


NASI -5883-3 


Unassigned (no Igniter) 


E5-153 


NASI -5883-5 


Canceled 


E6-I56 


NASI -5883-5 


Canceled 


E5-157 


NASI -5883-5 


Canceled 


E5-158 


NASI -5883-5 


Canceled 


E5-159 


NASI -5883-5 


Canceled 


E5-160 


NASI -5883-3 


(Repl. E5-14^) (Cancel) Case Tested 


E6-I6I 


NASI -5883 


Unassigned (Repl. E6-142) 


TABLE 


XXII 1(b) - HERCULES 


INCORPORATED 




AlcyotK 


e (BE3-A9) 


NUMBER 


CONTRACT 


USE 



AN09/003 
ANO9/OO5 
ANO9/OO6 
ANO9/OO8 
AN09/010 



NASI -71 02 
NASI -71 02 
NASI -71 02 
NAS 1-71 02 
NASI -71 02 



S-191 

Test/Shelf Life 
Air Force 
Air Force 
Germany 



ORIGINAL PASS jS 
OF POOR QUALITY 



80 





TABLE XXIV - 


NUMBER 


Contract 




20002 


AF04(695] 


-588 


20003 


AF04(695) 


-588 


20004 


AF04(695] 


-588 


20005 


AF04(695] 


-588 


20006 


AF04(695] 


-588 


20007 


AF04(695] 


-588 


20008 


AF04(695] 


-588 


20009 


AF04(695] 


-588 


20010 


AF04(695J 


-588 


20011 


AF04(695] 


-588 


^ 20012 


AF04(695] 


-588 


20013 


AF04(695; 


-588 


20014 


AF04(695; 


-588 


20015 


AF04(695] 


-588 


20016 


AF04(695; 


-588 


20017 


AF04(695; 


-588 


20018 


AF04(695; 


-588 


20019 


AF04(695; 


-588 


20020 


AF04(695; 


-588 


20021 


AF04(695; 


)-588 


20022 


AF04(695' 


)-588 


20023 


AF04(695; 


-588 


20024 


AF04(695 


1-588 


20030 


AF04(695 


)-588 


20031A- 


AF04(695' 


-588 


20032 


AF04(695' 


)-588 


-w-20033 


AF04 (695 


)-588 


20034 


AF04(695 


)-588 


20035 


AF04(695 


)-588 


20036 


AF04(695 


)-588 


20037 


AF04(695 


)-588 


20038 


AF04(695 


)-588 


20039 


AF04(695 


)-588 


B1 


AF04(695 


)-588 


30101 


AF04(695 


)-588 


30102 


AF04(695 


)-588 


30103 


AF04(695 


)-588 


30104 


AF04(695 


)-588 


30105 


AF04(695 


)-588 


Vc30104 Empty Case t 


S- 


'■oVTraded 


for X258E6- 


133. 


Vw'nVReplace 


30209 with 


2218 



UNITED TECHNOLOGY MOTOR HISTORY, ALTAIR I I |A, 
Altair III (FW4S) History 



USE 


NUMBER 


CONTRACT 


USE 


Test-AEDC 


30201 


NASI 


-5883 


S-150 


Test-AEDC 


30202 


NASI 


-5883 


S-153 


Test-AEDC 


30203 


NASI 


-5883 


Reject 


Test 


30204 


NASI 


-5883 


S-151 


Reject 


30205 


NASI 


-5883 


Test-LRC 


Test 


30206 


NASI 


-5883 


S-152 


Test 


30207 


NASI 


-5883 


S-159 


Reject 


30208 


NASI 


-5883 


Test 


Reject 


30209 


NASI 


-5883 


Rejectvrfov 


Reject 


30210 


NASI 


-5883 


S-158 


Reject 


30211 


NASI 


-5883 


Case Rejected 


Reject 


30212 


NASI 


-5883 


Case Rejected 


Case-Test 


30213 


NASI 


-5883 


Case Rejected 


Test-Loads 


2218-8(30214) 


NASI 


-5883 


S-160 


Test 


2218-9(30301) 


NASI 


-5883 


Test-AEDC 


Test 


2218-10(30302) 


NASI 


-5883 


S-l6l-''-VnV 


Test 


2223-1 


NASI 


-5610 


S-I67 


Test 


2223-2 


NASI 


-5610 


S-168 


Test 


2223-3 


NASI 


-5610 


S-174 


Air Force 


2223-4 


NASI 


-5610 


S-I65 


Reject 


2223-5 


NASI 


-5610 


S-I69 


Reject 


2223-6 


NASI 


-5610 


S-172 


Test-AEDC 


2223-7 


NASI 


-5610 


S-177 


Test-AEDC 


2223-8 


NASI 


-5610 


S-144 


S-145 


2223-9 


NAS 


1-5610 


S-171 


Air Force 


2223-10 


NAS 


-5610 


S-175 


Delta 


2223-11 


NAS 


1-5610 


S-166 


Air Force 


2223-12 


NAS 


1-5610 


S-I83 


Test-AEDC 


2223-13 


NAS 


1-5610 


S-185 


Air Force 


2223-14 


NAS 


1-5610 


S-173 


Reject 


2223-15 


NAS 


1-5610 


S-180 


S-131 


2223-16 


NAS 


1-5610 


S-I63 


S-147 


2376-1 


NAS 


1-7199 


S-182 


Case-Test 


2376-2 


NAS 


1-7199 


S-181 


Hydroburst 


2376-3 


NAS 


1-7199 


S-191 


Hydroburst 


2376-4 


NAS 


1-7199 


S-190 


Test- Loads 


2376-5 


NAS 


1-7199 


S-170 


-Test-AEDC 


2376-6 


NAS 


1-7199 


S-186 


S-148 


2376-7 


NAS 


1-7199 


S-188 




2376-8 


NAS 


1-7199 


S-184 



144. 



ORt^U-i^L PAGE [3 
OF POOR QUALITY 



81 





TABLE XXV - THIOKOL (ELKTON) 


TEM640 ALTAIR II |A 












HISTORY 








Number 


Contract 


Use 


Number 


Contract 


Use 


TCC-E-00 


NAS1-1 


11400 


TCC Test 


TCC-E-27 


NASl-1 


4200 


S-202 


TCC-E-01 


NASl-1 


1400 


AEDC Test (Failed) 


TCC-E-28 


NASl-1 


4200 


AEDC Test 


TCC-E-02 


NASl-1 


1400 


AEDC Test (Failed) 


TCC-E-29 


NASl-1 


4200-2 


S-198 


TCC-E-03 


NAS1-1 


11400 


Reject-Tested 


TCC-E-30 


NASl-1 


4200-2 


NRL 


TCC-E-04 


NASl-1 


1400 


Reject 


TCC-E-31 


NASl-1 


4200-2 


Unass igned 


TCC-E-05 


NASl-1 


1400 


Reject-NDT 


TCC-E-32 


NASl-1 


4200-4 


Assigned S-199 


TCC-E-06 


NASl-1 


1400 


Reject-NDT 


TCC-E-33 


NASl-1 


4200-4 


Unass igned 


TCC-E-07 


NASl-1 


1400 


Test-F Demo 


TCC-E-34 


NASl-1 


4200-4 


Unass igned 


TCC-E-08 


NASl-1 


1400 


Test-Demo 


TCC-E-35 


NASl-1 


4200-4 


Unass igned 


TCC-E-09 


NASl-1 


1400 


Q.ual . Test 


TCC-E-36 


NASl-1 


4200-4 


NRL 


TCC-E-10 


NASl-1 


1400 


Reject 


TCC-E-37 


NASl-1 


4200-4 


NRL 


TCC-E-11 


NASl-1 


1400 


Test (AEDC) 


TCC-E-38 


NASl-1 


4200-7 


Unass igned 


TCC-E-12 


NASl-1 


1400 


Test (RPL) 


TCC-E-39 


NASl-1 


4200-15 


Unass igned 


TCC-E-13 


NASl-1 


1400 


S-187 


TCC-E-40 


NASl-1 


4200-15 


Unass igned 


TCC-E-14 


NASl-1 


1400 


S-189 


TCC-E-41 


NASl-1 


4200-15 


Unass igned 


TCC-E-15 


NASl-1 


1400 


S-195 


TCC-E-42 


NASl-1 


4200-15 


Unass igned 


TCC-E-16 


NASI-' 


1400 


S-194 


TCC-E-43 


NASl-1 


4200-15 


NRL 


TCC-E-17 


NASl-1 


1400 


S-197 


TCC-E-44 


NASl-1 


4200-15 


NRL 


TCC-E-18 


NASl-1 


1400 


S-196 


TCC-E-45 


NASl-1 


4200-15 


NRL 


TCC-E-19 


NASl-1 


1400 


S-193 


TCC-E-46 


NASl-1 


4200-15 


Unass igned 


TCC-E-20 


NASl-1 


1400 


S-200 


TCC-E-47 


NASl-1 


4200-15 


Unass igned 


TCC-E-21 


NASl-1 


1400 


S-179 


TCC-E-48 


NASl-1 


4200-15 


Unass igned 


TCC-E-22 


NASl-1 


1400 


HE Test 


TCC-E-49 


NASl-1 


4200-15 


Unass igned 


TCC-E-23 


NASI-^ 


4200 


S-201 


TCC-E-50 


NASl-1 


4200-15 


Unass igned 


TCC-E-24 


NASl-1 


4200 


NRL 


TCC-E-51 


NASl-1 


4200-15 


Test 


TCC-E-25 


NAS1- 


14200 


S-192 


TCC-E-52 


NASl-1 


4200-15 


NRL 


TCC-E-26 


NAS1- 


14200 


S-203 


TCC-E-53 


NASl-1 


4200-15 


NRL 










TCC-E-54 


NAS1- 


14200-21 


Unass igned 



83 



CHAPTER IV - SCOUT VEHICLE SYSTEMS 



PRECEDING PAGE BLANK NOT FILfwI^ 



GUIDANCE AND CONTROL 

The guidance and control system provides an attitude reference and the resultant 
control signals and forces necessary for stabilization of a vehicle in its three 
orthogonal axes corresponding to pitch, yaw, and roll during vertical probe, 
reentry, or orbital flight programs. Figure kS illustrates the guidance and 
control systems. 

The roll axis is maintained at the launch reference while the pitch axis is 
programmed through a preselected angle corresponding to the desired vehicle zero- 
lift trajectory. The yaw axis may remain at launch reference or may be programmed 
through a preselected angle corresponding to the desired orbit inclination angle. 
Miniature integrating rate gyros contained within the inertial reference paclcage 
detect any angular deviation about the vehicle programmed path and generate pro- 
portional error signals. These error signals are then summed with corresponding 
rate signals and are transmitted to the appropriate control subsystem such that 
the vehicle is continuously programmed to the gyro reference axis. 

In addition to the "strapped down" gyro sensors, the system contains a relay 
unit for power and ignition switching, an intervalometer to provide precise 
scheduling of events during flight, a programmer to provide torquing voltages 
to the pitch or yaw gyro, an electronic signal conditioner to convert the gyro 
outputs to proper control signals, and the associated 400-cycle inverter and D-C 
batteries. An optional roll and yaw compensation unit that reduces flight path 
errors in the roll and yaw plane is available. Figure ^9 illustrates the location 
of the controls. 

A fourth-stage attitude and control system was flown on Scout-E with the Hawkeye 
m i s s i on . 

FIRST-STAGE CONTROLS 

In the lift-off configuration, the vehicle is aerodynamics I ly stable. A propor- 
tional control system featuring a combination of jet vanes and aerodynamic tip 
control surfaces operated by hydraulic servo actuators is used to control the 
vehicle throughout the entire first-stage burning period. The jet vanes provide 
the majority of the control force during the thrusting phase. The aerodynamic 
tip controls provide all the control force during the coasting phase following 
burnout of the first stage. 

SECOND- AND THIRD-STAGE CONTROLS 

Second- and third-stage control systems as sketched in figure 50 are based on 
the same concept of operations as the first stage but differ in the method used 
to generate the control force. The control forces for these two stages are 
provided by hydrogen peroxide reaction jet motors which are operated as an 
"on-off" system. The motors are so placed that moments are set up about each 
of the three axes: pitch, yaw, and roll. The motors are mono-propel lant and 
utilize 90 percent hydrogen peroxide (H2O2) . Propel lant pressur izat ion is 
provided by compressed nitrogen (N2) gas. Design characteristics of the thrust 
motors and H2O2 tankage capacity are shown in table XXVI. 



ORIGINAL PAGE m 
OF POOR QUALITY 



A 



85 



GROUND POWER 



01 

3 

D 



D 
en 



SPIN 
TABLE 



GUIDANCE components 



CONTROL. 
VALVES 



3 AXI S 

RATE 

DAMPING 



REACTION 
JETS 



^ 



IZH 



A 



M 



^LMS^Jh. 



CONTROL 
VALVES 



X 1) 



<y 



ROLL 



REACTION 
JETS 



<■ 




STATIC 
INVERTER 






BATTERI ES 



3 AXIS MIG 
REFERENCE 
SYSTEM 



GYRO 
CAGING 
CONTROL 



IL 
u 



PITCH 
PROGRAMMER 



ROLL* & YAW 
COMPENSATOR 



*Optional 



YAW 



GROUND TEST 
SIGNALS 



PITCH 



(gK 



SERVO- _-*V Y 

AMPLIFIERS 



/I 



SERVO 




ELECTRO 


POWER 




HYDRAULIC 


SUPPLY 




ACTUATORS 



SURFACE 
POSITION 
FEEDBACK 



N 



Figure kS.- Guidance and control systems, 



86 



ORiGI^^AL 



'(■"AS'. 



IS 



OF POOR QUALITY 









RAYI.OAO 



UPPER HO" 



4TH STAGE SPIN-UP ROCKETS 
AND GUIDANCE PACKAGE 



LOWER aon 



TRANSITION 



UPPER ac ■ 



» » 



^ 



3RD STAGE CONTROL SYSTEM 
AND RATE GYROS 



l-OWER «CB 



.TRANSITION 



REACTION THRUST SYSTEM ■ 



HYDROOEN PEROXIDE (H2 Oj) UIQUID 
TRANSMISSION SY8TISM - 2ND AND 
3RD STAOE ATTITUDE CONTROI. IN 
PITCH, YAW AND ROL.L. 



UPPER HB" 



2ND STAGE CONTROL 
SYSTEM 



L.OWER "B* 



TRANSITION 




PRESSURIZING 
OAS STORAGE 



HYDRAUI-ICAL1.Y POSITIONED JET VANES AND 
AERODYNAMIC OEI-TA TIP SURFACES ON A 
COMMON SHAPT 




1ST STAGE CONTROL SYSTEM 



.BASE MA" 




Figure ^8.- Location of controls. 



TOWER SIDE 



40 l_B. MOTOR (4) 



87 



ORIGINAL PAGc 13 
OF POOR QUALITY 



PITCH AXIS 



N TANKS (2) 




PITCH 
AXIS 



YAW AXIS 
TOWER SIDE 



14 UB ROUU 
MOTOR (4) 

H TANKS (10) 
2 2 



500 l_B. MOTOR (4) 



A, SECOND STAGE 
SYSTEM ARRANGEMENT 




40 UB. REACTION 

CONTROL MOTORS (k) 

H O TANKS (2^ 

2 2 * •* 



N TANKS (2) 



- YAW AXIS 

2 1_B REACTION 
CONTROL. MOTOR (2) 



B. THIRD STAGE 
SYSTEM ARRANGEMENT 



Figure 50.- Second and third-stage controls. 



FOURTH-STAGE SPIN-UP SYSTEM 



The fourth stage which Includes the payload, receives the proper spatial orien- 
tation from the control exerted by the first three stages after which it is 
spin-stabilized by a combination of four impulse spin motors. The miniaturized 
rocket spin motors are mounted tangential ly in the skirt at the base of the 
fourth stage. Spin up begins approximately 6 seconds prior to fourth-stage 
ignition. Spin motor arrangement and characteristics are shown in figure 51. 
Spin rate at fourth-stage ignition and burnout for various roll moments of 
inertia are given in figure 52- This figure gives the spin rate with two motors. 
The spin rate for four spin motors of the same size is double the spin rate for 
the two, and the spin rate of four motors of two difference sizes is the sum of 
the spin rate for the different motors. (See example in figure 52.) 



TOWER SIDE 




4TH STAGE HEAT SHIEI_0 



SPIN MOTOR 



VAW AXIS 



FOURTH STAGE SPIN-UP SYSTFM 







SPIN 


MOTOR CHARACTERISTICS 








Thrust Vacuum, Pounds 
Burning Time, Seconds 
Total Impulse Vacuum, lb-sec 


OPERATING TEMPERATURE 




20° F 




70° F 


1300 F 


eKSitO-HA 


IKSW-HA 


IKS75-HA 


.6KSW-HA 


IKSl^-HA 


1KS75-HA 


.eKSi^O-HA 


1KS40-HA 


1KS75-HA 


0.70 
29.9 


I46.O 

1.06 
52.0 


67.0 
1.03 
75.0 


42.3 

0.69 
29.2 


kS.2 

1.08 
'(8.9 


70.0 

1.0 

75. "t 


50.8 
0.659 
30.0 


52.0 
0.96 
53.0 


73.0 
0.98 
75.8 



Figure 5I .- Spin Motor Arrangement and Characteristics. 



88 



ORIGINAL PAGE !S 
OF POOR QUALiTV 



TABLE XXVI - GUIDANCE AND CONTROLS. 



Design Characteristics 


Second Stage 


Third Stage 


ROCKET MOTORS 
Thrust Levels 


500- lb. Motor 
510 + 30 lbs. ^ 

490 + 30 lbs. A A 

40- lb. Motor 
46 :!: 6 lbs. A 
44 :!: 4 lbs. A A 


60- lb. Motor 

60.3 
14- lb. Motor 

1^^ (2-5) „^. 

3+1.0 lb."" 
2- lb. Motor 

2.a : iS;Ei 


Total Impulse Required 
100% Duty Cycle 
Intermi ttent 


25,560 lbs. -sec. 
21 ,300 lbs. -sec. 


2,560 lbs. -sec. 
2,240 lbs. -sec. 


Specific Impulse (Steady) 
Ib^ - sec 


500 # - 155 
40 # - 166 


60 # - 160 

14 # - 168 

2 # - 161 


m 


Coast Time 


''7'?^ , 5 sec. 
Orbital 

Re-entry 250 sec. 


Pi-obe 20 sec. 
Re-entry 

Orbital 600 sec. 


Weight - lbs. 


500 # - 15-5 lbs. max. ea . 
40 # - 2.3 lbs. max. ea . 


60 # - 2.78 lbs. max. ea. 

14 # - 1 .88 lbs. max. ea. 

2 # - 1 .50 lbs. max. ea . 


HYDROGEN PEROXIDE 
TANKAGE CAPACITY 

Weight Hydrogen 
Peroxide - lbs. 


182 


18,2 


Volume Hydrogen 
Peroxide Tankage 
cu. in. 


3.840 


384 


A Condition No. 1 . 


One 500 lb. motor and two 40 


b. motors firing. 



A A Condition No. 2. Two 500 lb. motors and two 40 lb. motors firing, 
* Roll motor thrust control level during main stage engine burning, 
'^ Roll or yaw motor thrust control during vehicle coast. 



Q. 



in 

tr 
o 

\- 
o 

z 

Q. 
(/) 

O 

I- 

ir 
o 

z 
o 

Z 

I- 
< 

LiJ 
I- 
< 



a 

V) 

Q 
LU 
i— 
U 

D 
UJ 

tr 
a. 



ITEMS 

FW-4S 

FOURTH STAGE MOTOR 
UPPER 'D* SECTION 
SPIN TABLE 
STANDARD 'E* SECTION 
SEPARATION SYSTEM 
TOTAL LESS PAYLOAD 

PAYLOAD 

FOURTH STAGE SPIN-UP 
ITEMS 



+( 
( 



89 




(SLUG-FT2) 


ORIGINAL PAUc IS 




OF POOR QUALITY 


7.10 




.40 




.90 




.16 




8.56 
) 





) 



180 



NOTES: 1. RADIUS OF SPIN MOTOR THRUST = 11.16 INCHES 

2. MAXIMUM FORCE: A. 1KS40 AND 0.6KS40 = 75 LBS. 

B. 1KS75= 91 LBS. 



160 



140 



120 



100 



80 



60 



40 









"^ 


s 
















"* 




"^ 














—" 












— 


— 


— 






— 




— " 






— 




n 












s 




















t.Ay-vivii-i_i:^. 1. r »Y— to rkJUK 1 M i 1 Mljt MU 1 UK 

2- IrOLL = 1.44 SLUG-Ft2 (PAYLOAD) 
3. lorM 1 ""10 SLUG-Ft2 














s 
















- 
















s 












(FOURTH STAGE SPIN-UP) 


















s 


V 












4. SPIN MOTOR CONFIGURATION 




















\ 


s. 










MOTORS SPIN RATE 
























S 








NO. TYPE RPM 


























V 


V 




2 0.6KS40 47.1 




























■^ 


s 




^ ir\b/:D ^ii^,3 


i 


W — 




























s 


K 












- 


— 






1 1 1 1 


1 D3.»+ 
ll 1 1 1 






M 






\, 
































S 


s 










































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— 




■ « 


— 


- 


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- 


— 




^ 


s 






































~ 








S 


w 






















— 


-- 










s 


s, 


> 


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s 


t^'^ 


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kit. 


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13 14 

FOURTH STAGE ROLL MOMENT OF INERTIA (INCLUDING PAYLOAD) - SLUG-Ft2 

(SLUG-FT2 = 0.737 X KG-M^) 



Figure 52.- Spin rate at fourth-stage ignition and burnout 
for various roll moments of inertia 




ORIGINAL PAG?^ 
OF POOR QUA^*^ 



90 



STAGE SEPARATION SYSTEM 



The Scout vehicle four sol id-propel lant rocket motors are joined by interstage 
structures referred to as "transition sections" as described in table IV. 
Each transition section is divided into upper and lower portions at the stage- 
separation plane. Frangible "blow-out" diaphragms (figure 53^ join the first 
and second, and the second and third stages. The diaphragm forms an internal 
clamp by the threaded periphery that engages two structural threaded rings at 
the separation plane. Blast pressure of the upstage motor ruptures the 
diaphragm, disengaging the periphery and allows the stage to separate. The 
third and fourth stages are joined by a "cold-separation" arrangement of 
springs held compressed by a securing clamp (figure 53). Explosive bolts 
release the clamps, effecting separation by this method also. The fourth-to- 
fifth stage separation system is of similar design in the five-stage Scout 
configuration. Note the position of the separation systems in figure 2k. 



SEPARATION 
CLAMP 




FOURTH-STAGE 



EXPLOSIVE BOLT (4 



EJECTOR SPRING (32) 



SPIN ROCKET (4) 



THIRD-STAGE 



SPIN BEARING 




Figure 53.- Spring ejection separation system. 



91 

ELECTRICAL POWER AND IGNITION SYSTEM 

To achieve reliability, dualized ignition systems have been employed as illus- 
trated in figure 54. Safety features have been designated into the systems to 
prevent accidental or premature firing of the rocket motors. Dual squibs are 
used in all igniters, where each one of the squibs is in a separate circuit 
and is connected to a separate battery so that an electrical component failure 
will affect only one circuit. Ignition of the first-stage motor is accomplished 
by a direct electrical signal provided by launch blockhouse command. Second-, 
third-, and fourth-stage ignitions are controlled by the guidance program timer. 
The system provides for the following firing sequence: first-stage ignition 
from blockhouse command, second-stage ignition, payload heat-shield ejection, 
third-stage ignition, spin motors, fourth-stage squib ignition, and fourth- 
stage separation. The same primary power source is utilized by the ignition 
and the destruct systems. Fifth-stage ignition (when applicable) is controlled by 
a single independent ignition system. 

The ignition system contains automatically-activated silver-cell battery packs, 
timer-actuated control relays, and safe-arm latching relays for arming the heat 
shield; spin motors; separation bolts; and motor igniter circuits. Squibs for 
all stages are insertable through removable side panels on the vehicle. 

The 23-003793 initiator (figure 55) was used in the Algol II, Algol MA, and 
Castor II rocket motors. The initiator has a steel case containing the bridge- 
wire, electrical pins, ceramic seal, insulators, primer explosive charge, main 
explosive charge and moisture closures. A bridgewire is attached to pins A-B. 
The pins and ceramic assembly are bonded into the case. The primer charge is 
molded around the bridgewire inside an insulator cup. The main explosive charge 
is insulated from the case and primer charge and sealed with Mylar. The case is 
sealed with another closure and crimped and bonded into place. 

The Antares (250) rocket motor igniter squib, Hercules Powder SD6OEO is shown 
in figure 56. This unit has the explosive train enclosed in a bronze case 
crimped within the main steel body. The bronze case contains the bridgewires 
and detonation charge, delay fuse (1.5 to 1.7 seconds), main charge, and weather 
closure. 

The Altair II (X258) and Altai r III (FW-4S) rocket motors use the Hercules 
Powder SD6OAI initiator (figure 56). This unit is similar to the SD6OEO except 
that the steel exterior case is much longer to accommodate a longer delay fuse 
(5.5 to 7.24 seconds). 



DESTRUCT SYSTEM 

Radio command destruct, PAM/FM/FM telemetry and radar tracking comprises the 
Scout vehicle R/F systems. The UHF radio command destruct system provides 
capabilities for positive thrust termination of the Tirst three stages to 
avoid a live uncontrolled vehicle impacting on or near the ground launch 
facilities or in a populated area. The destruct system is designed to comply 



ORIGINAL PAGE IS 
OF POOR QUALITY 



92 



SPIN MOTOR 
I GN I TORS 




4TH STAGE 
I GN I TORS 



HEAT 
SHIELD 



3RD STAGE 
IGNITORS 



3RD AND 4TH 

STAGE 
SEPARATION 

BOLTS 



D SECTION 
ARMING BOX 



■ .• «i»WH ; 



IGNITION 

BATTERY 

(2) 



12 POSITION 
LEDEX BOX 



2ND STAGE 
IGNITORS 



C SECTION 
ARMING BOX 



•^ 



POWER 

CONTROL 

RELAY 

BOX 



28 V 
BATT 



_J TIMER j 



2ND 
STAGE 



1ST STAGE 
IGNITORS 



B 

SECTION 

ARMING 

BOX 



1ST 
STAGE 



ii 



IGNITION 
FLYAWAY 



37 V 
BATT 



INTERLOCK 



MONITOR 

FLYAWAY 

(2) 



BASE A 

28 V 

BATTERY 



Figure 5^.- Ignition system block diagram. 



OR/GINAL PAGE m 
OF POOR QUALITY 



93 



BODY 



PROPELLANT GRAIN 




TRAP 
CLOSURE DISK 



EXPLOSIVE MIX 



CLOSURE DISK 




Figure 55.- 23-003793 Initiator Assembly. 



SD60AI INITIATOR WITH ADAPTER 



IGNITOR 
ADAPTER 



CLOSURE 




CLOSURE 



VIEW A-A 



Figure 5^.- Hercules Initiator Assembly Details. 



9^^ 



OF POOR Q;. A1-?TY 



with the requirements of both the Wallops Station and Western Test Range. The 
system provides two methods of destruct; the command method operated by R/F link, 
and the automatic method utilizing lanyard and pressure-actuated switches. The 
vehicle has two completely independent destruct systems consisting of antennas, 
power supplies, command receivers, and pyrotechnics. Each system has a pair 
of flush-mounted "bow-tie" antennas diametrically opposed on transition "C" 
section. These are connected through a coaxial cable and a tee divider to a 
Motorola MCR-151 four-channel command receiver with an integral decoder. The 
output of the decoder is connected through a J-box to the destruct relay box 
and then to the stage pyrotechnic devices. The system is compatible with the 
AN/FRW-1 transmitter which has a nominal R/F power output of 500 watts. A 10-kw 
power amplifier and directional antenna of l4-db gain are available at the WTR 
and Wallops Station launch sites. Throughout the portion of the flight where 
command destruct is required, the Range Safety transmitter (AN/FRW-2) is 
required to transmit continuously and the carrier frequency modulated by one 
IRIG channel. In the vehicle, the particular decoder relay associated with 
that channel is monitored by the instrumentation system. Command destruct may 
be initiated at any time after launch as the pyrotechnics are armed by hard 
line prior to launch. The actual destruct command requires the AN/FRW-2 
transmitter be modulated by three IRIG channels in the proper sequence, thus 
reducing the probability of an inadvertent destruct command, as well as the 
probability of extraneous signals causing destruct. 

Electrical and mechanical safing is provided for ground operation. Destruct 
of the vehicle may be accomplished by R/F link at the discretion of the range 
safety officer or by the automatic system if the vehicle were to "break up" 
during flight. Destruct capabilities for the payload can be incorporated if 
desired. New receivers were incorporated into the Scout vehicle in early 1973- 
The new receiver was a Motorola MCR-151-M, four-channel, narrow bandwidth with 
an integral decoder. A simplified diagram of the system is depicted in figure 5 7- 
Figure 58 shows Scout vehicle S-110 a few seconds after takeoff. This vehicle 
was destructed due to first-stage nozzle failure and is shown as photographed 
by the tracking camera. 



WD STG. 

PRESSURE 

SW. 



15T STG 
PRESSURE 



2ND 

STG. 

LAN. S*. 



1ST 

STG. 

LAN. SW. 



DEST 

23v 



SHAPED 
CHARGES 



SAFE/ARM 
UNIT 



DESTRUCT 

POWER (5) 

24V-OC 

r 



DEST 
2 



RELAY 
BOX 



SAFE 'ARM 
CONTROL 



RECEIVER 
POWER (2) 
28V 



Tsnr 



JUNCT 
BOX 



28V 
INTER 



T/M MONITOR 



2ev 

INTER 



T'M MONITOR 



A 



Fi gure 57 .- Destruc t system. 



95 



OF POOR QUALITY 




Figure 



58.- Scout vehicle 110 at k.7 seconds after takeoff. 
INSTRUMENTATION 



The instrumentation system for the Scout vehicle includes vehicle-borne 
equipment required to provide ground monitoring of subsystems during prelaunch 
checkout and countdown, telemetry monitoring of the flight performance of all 
four stages, radar beacon tracking, and command destruct electronics for 
receiving and decoding of command destruct information. The telemetry system 
for the first three stages of the Scout vehicle is a standard IRIG PAM/FM/FM 
system capable of handling 20 standard IRIG subcarrier channels. The vehicle 
telemetry transmitter is a Conic CTM/UHF BOS-LTV operating at 2230.5 megahertz. 
The nominal R/F power output is 5 watts delivered to three equally spaced 
externally mounted swept back blades on lower "D" section. Signal voltages 
for a number of measurements, both analog and ON-OFF types, are derived directly 
from basic components such as the guidance system, control system, and the 
destruct system. A simplified diagram of the system is depicted in figure 59.. 
The telemetry system for the fourth stage of the Scout vehicle is a standard 
IRIG FM/FM system capable of handling 12 standard IRIG subcarrier channels. 
The transmitter is a Vector T-105S operating at 2210.5 megahertz. The nominal 
R/F power output is 5 watts delivered to a wraparound antenna externally 
mounted on upper "D" section. Signal voltages for the analog measurements are 
derived directly from basic components. 



96 









MEASUREMENT 
INPUTS 



TEMPERATURES 



PRESSURE 
TRANSDUCERS 



ACCELERATIONS 



GUIDANCE SYS. 
PARAMETERS 



REFERENCE 

VOLTAGE 

SUPPLY 



SIGNAL 
CONDITIONER 



DISTRIBUTION 
CONTROL NET 



BOOST STAGE 
PARAMETERS 



VARIOUS ON-OFF 
SIGNALS 



VOLTAGE 
CALIBRATOR 



— COMMUTATOR 



SUB-CARRIER 

OSCILLATOR 

PACKAGE 



J_ 



MIXER 



V 



FM-FM 
TRANSMITTER 



Figure 53.- Simplified diagram of instrumentation system. 



97 



RADAR TRACKING BEACON SYSTEM 



The radar beacon employed on the Scout vehicle has been changed from the Vega 
Precision Laboratories, Inc., Model 302C-2A-2 to the Motorola SST-171C radar 
beacon. The beacon has a nominal peak R/F power output of 500 watts, single 
pulse. The beacon antenna has been changed from an H-plane sectoral horn to 
the Vega Precision Laboratories, Inc., model D^OOZ^I G blade antenna. The 
antenna is mounted externally on lower "D" section. The main lobe of the 
radiation is aft along the vehicle roll axis so that tracking by the Range 
AN/FPS-I7 instrumentation radar operating in the beacon mode is limited to 
within a few degrees aft of the vehicle along the flight path. The radar 
tracking data are generally available up to ignition of the fourth stage at 
all ranges. Technical data on all Scout systems have been published on the 
following subjects. 



(A) 



(B 
(C 
(D 
(E 
(F 
(G 
(H 
(I 
(J 



(K 

rev is io 
(L 
(M 
(N 
(0 
(P 

(a 

(R 
(S 
(T 
(U 
(V 
(W 
(X 
(Y 



ns, 



Aerodynamic design data 

(1) Stability and performance analysis data 

(2) Structural design data 
Performance trajectory 
Stress analysis 

Loads and Dynamics 
Guidance system analysis 
First-stage control system analysis 
We ights 

Thermal protection analysis 

Reaction thrust systems 

Destruct system 

Procurement, environmental, and acceptance test specifications and 

User's Manual 

Historical summary 

Standardization and configuration control operating procedures 

Rocket motor and pyrotechnics manual 

Feasibility study of a Scout central ordnance complex 

Development of electrostatic sensors 

Tracking radar data 

Vehicle performance telemetry records 

Vehicle log book 

Quality and reliability documentation 

Vehicle vibration data 

Instrumentation calibration summary 

Spares report 

Final flight trajectory 



99 



CHAPTER 5 - SCOUT RELIABILITY AND QUALITY ASSURANCE PROVISIONS 



PRECEDING PAGE BLANK NOT FILMED 



100 



PURPOSE 



The purpose of the Scout Reliability and Quality Assurance Programs is to 
assure attainment of specified inherent reliability goals for the vehicle 
system and to further assure that operational reliability is maintained 
throughout the Scout program. The vehicle system's flight reliability objec- 
tive is 0.95 as defined by the Flight Success patio. Figure 60 is a photograph 
of flight S-122 which was the first launch upon completion of the development 
and prototype programs and the beginning of the production recert if icat ion pro- 
gram that elevated the success ratio above 0.94(i). Figure 61 is a photograph 
of flight S-187 which extended the world record for consecutive successful 
launches of a major missile system to 35 in a row. This was the sixty-fourth 
successful launch out of sixty-seven attempts since the recer i t if icat ion 
program. The thirty-sixth and thirty-seventh continuous successes in a row 
were Phase VI I vehicles. 



PLANS 

The Scout Project Office, through periodic reports prepared by the Contractor 
by maintaining continuous review of reported equipment malfunctions, and contin- 
uous design review, assesses the Scout system reliability. In order to provide 
the necessary information to enable the Scout Project Office to maintain this 
close surveillance, the items listed below are necessary and available. 

PRINCIPAL ELEMENTS 

(A) Reliability Program Plan 

(B) duality Program Plan 

(C) Rel iabil ity Analysis of: 

(1 ) Ignition System 

(2) Destruct System 

(3) Guidance and First-stage Control System 
(k) Reaction Control System 

(5) T/M System 

(6) Heat Shields 

(7) Hydraulic Control System 

(8) Radar Beacon 

(9) Separation System 

(10) Propulsion Systems 

(11) Structure , _. 

(D) Quarterly Reliability Status Reports 

(E) Environmental Test Program 

(F) Environmental Test Reports 

(G) Reliability Review Meetings 

(H) Qualification Status Report (Summary of Status and History Files) 

I Reliability Data Reporting (Malfunction Reporting System) 
(J) Continuous Design Review 

and pifL^^^'i""°"' Monitoring by NASA (including review of budget, schedule, 
and effort to be accomplished on each identifiable task). 



^ 'Details in Chapter 5. page 113 



toi 









Figure 60.- Launch of Exploret XIX 



ORIGINAL PAGr 
BLACK AND WHITE PHOTOGRAPI-r 




Figure 61(a).- UK-5 ready for launch at 
San Marco on Octpber Ik, 



Figure 61(6).- S-lS? with UK-5 payload 

on the launcher at San Marco. 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



103 



(L) Rel iabil ity Audits 

(M) Equipment Logs 

(N) Malfunction Reporting System (including Failed Parts Analysis Reports) 

(0) Field (iual ity Plan 

(P) Semi-Monthly Narrative Status Reports 

APPLICATION 

The quality assurance, reliability, and environmental test programs that are 
currently programed with the vehicle prime contractor evolved from Amendment 18 
of contract NASl-1295, which in turn had replaced the temporary reliability 
program of contract NASl-900. Since then the program has continued under 
NAS1-466if, NAS1-6020, NASl-7256, NAS1-10000, NASl-12500, NAS1-15000, and 
projected to NAS1-16200. The assessed design goals for the Scout systems are 
itemized in table XXVII. The reliability practices and activities accomplished 
under the reliability program, include the following. 

PROGRAM COORDINATION 

Reliability program coordination is provided to fulfill the requirements of the 
Reliability Program Plan, to assure that the required inherent reliability is 
designed into the vehicle system, and that operational reliability is maintained. 
This is accomplished by monitoring and reporting progress of the reliability 
program and other pertinent data for timely NASA and LTV management decisions. 
Periodic reliability progress review meetings are held as scheduled by the NASA 
Scout Project Office for the purpose of establishing the progress and status of 
the Reliability Program, and for the review and initiation of corrective action 
on existing and potential reliability problems. Vought submits quarterly 
Reliability Status Reports to NASA Scout Project Office. These reports provide 
information relative to the reliability status of the Scout vehicle and summarize 
the progress of the Scout Reliability Program during the preceding quarter. 

RELIABILITY ANALYSIS AND DESIGN REVIEW 

Quantitative reliability analyses are, or have been, performed on the following: 



(A 
(B 
(C 
(D 
(E 
(F 
(G 
(H 
(I 
(J 
(K 
(L 



Ignition System 

Destruct System 

Guidance and First-stage Control System 

Reaction Control System 

T/M System 

Heat Shields 

Hydraulic Control System 

Radar Beacon System 

Separation System 

Propuls ion 

Structure 

GFP (monitoring and liaison only) 



Scope of Analysis - Failure mode effects and critical ity analyses are 
revised and up-dated as necessary on a 1 1 systems listed above. Frequency of 



104 



TABLE XXVII - ASSESSED DESIGN GOALS FOR SCOUT SYSTEMS 







Reliabil 


ity Design 


Goals 




System 














First 


Second 


Third 


Fourth 


System 




Stage 


Stage 


Stage 


Stage 


Stage 


Propulsion 
Algol 
Castor 
Antares 
Altair M 


0.9960 


0.9950 


0.99^*0 


0.99A0 


0.9792 


Igni tion 


0.99995 


0.99995 


0.99995 


0.99995 


0.9998 


Destruct 


0.9999 


0.9999 


0.9999 




0.9997* 


Median ical 

Fins & Jet Vanes 


0.9996 








0.9987 


Stage Separation 

Diaphragm 

Spin Separation 




0.9999 


0.9999 


0.9999 

o.ggg'j 




Structural 


0.9997 


0.9999 


0.9999 


0.9999 


0.999^ 


Guidance (including 
first-stage contiol) 


0.9861 


0.9985 


0.9982 




0.9928 


Control 




0.9980 


0.9867 




0.9847 


Instrumentation 










0.9975 


Ground Systems 










0.99 



Vehicle Reliability 
Ry = RiR2R3R/fR5R6'^7'^8 

Rv = (-9792) (.9998) (.9987) (.999^) (.9928) (.9847) (.9975) (.9975) 
Rv = 0.9504 (Propability of successful Scout flight.) 

*Probability of successful destruct of first three stages. 




105 



functional failure analyses are performed on parts of systems deemed either 
to be marginal, or highly sensitive to this method of analysis, or whenever a 
need for detailed analysis is indicated. 

Design Review - In order to assist in attaining apportioned reliability 
goals, reliability engineers review all new and revised designs, drawings, 
specifications, and f ield/in-plant checkout procedures in coordination with 
design, manufacturing, checkout, and field operational groups. Basic design 
review activities to be performed as required to assure that reliability goals 
are met include: 

(A) Informal Design Reviews 

(B) Formal Design Reviews 

(C) Reliability Trade Studies 

(D) Component Application Analysis 

Single Failure Point Analysis - The Scout Single Failure Point Investiga- 
tion Program was conducted to analyze flight-critical systems of the Scout 
vehicle in 1973 to identify single failure point sources and determine the 
adequacy of the associated prelaunch testing and ground support equipoment. 
A single failure point source is defined as any single piece of hardware which 
could fail and cause loss of a Scout vehicle in flight. As a result of this 
investigation, 3k3 single failure point sources were identified for flight- 
critical systems. No single failure point sources were found which exhibited 
deficiencies that would require mandatory design corrective action. Some 
potential problem areas were disclosed in the adequacy of test procedures and 
ground support area. All potential problem areas have been investigated and 
the necessary corrective action implemented. (See Appendix B.) 

RELIABILITY DATA REPORTING 

Reliability data is accumulated, evaluated, and reported by implementation of 
the fol lowing: 

Malfunction Reporting System - The malfunction reporting system provides 
for reporting of all malfunctions that occur on the Scout Program at the then 
LTVAC/Vought Systems Division; at the field sites (Wallops Flight Center and 
Air Force Western Test Range); and on vendor-performed flight acceptance test 
results. The system further provides a controlled closed-loop corrective action 
mechanism. Data are processed by a coding and Automatic Data Processing System 
to assure complete histories in the evaluation of any given Scout component 
and/or system. Detail failure analyses are performed on failed components and 
equipment whenever an analysis is deemed necessary or advisable. This analysis 
results in identification of all deficiencies of the involved item. Positive 
corrective action is taken on all failures reported. Following completion of 
the failure analysis, and/or determination of the cause of failure, the required 
corrective action is accomplished. 

Reliability Status Report - In order to provide a periodic report of 
reliability status of the Scout vehicle systems, a status report is submitted 
quarterly. 



106 



RELIABILITY STUDIES 

Reliability Assessments - Early in the NASA Scout design program, the 
reliability of the Scout vehicle and the vehicle systems was assessed. The 
purposes of these assessments were first, to establish the feasibility of 
designing a vehicle of satisfactory reliability; and second, to establish the 
required reliability for each system and flight stage necessary to attain a 
desirable vehicle reliability. Reliability programing endeavors to assist in 
attaining and exceeding the established goals. In assessing system reliability 
and establishing design goals, realistic appraisal of design feasibility consid- 
erations includes these factors: 

(A) Proposed system design characteristics 

(B) System complexity 

(C) Hardware state of the art 

(D) Operating environments 

(E) Past experience with similar equipment and system 

(F) De-rating factor 

(G) Fl ight duration 

(H) Redundancy features 

(l) Ease of operation 

(j) Accessibility and maintainability 

Reliability assessments of Scout systems yield a vehicle reliability of approxi- 
mately 95 percent. 

Design Review in a Reliability Program - A reliability design review is an 
integral part of an overall reliability control program. The design review is 
an audit or evaluation of the logic and practicability of the basic design of 
equipment . It was conducted on the initial design concept and on all changes 
thereto. The design review is a planned, continuous monitoring of the capability 
of the equipment to meet the expressed performance and reliability requirements 
of the equipment during operational use. 

ENVIRONMENTAL TEST PROGRAM 

The Environmental Test Program reflects Scout systems flight acceptance test 
criteria and test program plans. The environmental criteria is based on actual 
flight environment and is up-dated as additional data becomes available. 

TEST REQUIREMENTS 

Component Functional Tests are performed on the items of table XXVIII and receive 
functional testing in accordance with the applicable Vought acceptance test speci- 
fication. Data and reports for these items are maintained. 

Component Flight Acceptance Tests are performed on such safety-of-f 1 ight items 
as are listed in table XXIX. Scout Standard Environmental Tests are performed 
on safety-of-f 1 ight items after which the requirements are reviewed with the 
NASA Scout Project Office for possible modification of component test require- 
ments based on performance in the test program and in flight. 



107 



OF POOR QUALITY 





TABLE XXVIII 


- COMPONfNT 


DATA 






Code 
No. 


Name 


Source 


Part Number 


Procurement 
Spec. No. 


Location 
in Vehicle 


No. per 
Vehicle 


001 


Electronic Inverter 


M-H 


DSG30E1 


304-579 


D Lower 


1 


002 


Diode Unit 


M-H 


DDG93B1 


304-580 


C Upper 


2 


003 


Poppet Valve Electronics 


M-H 


DEG211F2 


304-582 


D Lower 


1 


OOit 


Servo Ampl if ier 


M-H 


DEG233D1 


304-583 


A 


2 


005 


Programer 


M-H 


DRG87J1 


304-616 


D Lower 


1 


006 


Interval ometer 


T-l 


'»39900-3 


304-613 


D Lower 


1 


007 


Guidance Unit Assembly 


M-H 


DGG122F3 


304-617 


D Lower 


1 


008 


Rate Gyro Unit 


M-H 


DGG188E1 


304-585 


C Upper 


1 


009 


Power Switching Relay 
Unit 


M-H 


DRG95B1 


304-581 


A 


1 


010 


Hydraul ic Servo 
Actuator 


M-H 


DMG109E1 


304-618 


A 


4 


Oil 


Power Control Relay 
Box 


VSD 


23-00'il70 


- 


D Lower 


1 


012 


Radar Beacon 


VEGA 


SST-171C 


304-853 


D Lower 


1 


013 


Radio Command Receiver 


Motorola 


MCR-151M 


304-828 


C Upper 


2 


014 


Ignition Relay Assembly 


VSD 


23-004160 


- 


D Lower 


1 


015 


Ignition Relay Assembly 


VSD 


23-002068 


- 


C Lower 


1 


016 


Destruct Relay Assembly 


VSD 


23-00^*127 


- 


C Upper 


1 


017 


Solenoid Operated 
Rotary Switch 


Ledex 


23-002069 


304-639 


D Lower 


1 


018 


FM/FM Transmitter 


CTM 


23-003825 


304-783 


D Lower 


1 


019 


Relay Junction Box 
Transition C 


VSD 


401-10018-11 


- 


C Upper 


1 



020 Telemetry Package TD! 

Mixer Ampl if ier 
PAM Commutator Switch 
Subcarrier Oscillators 
DC Regulated Power Supply 

021 Resistor Box VSD 

022 Resistor Box VSD 

023 Rol 1 and Yaw Compensator VSD 

024 Body Bending Filter M-H 



I799A 



304-785 



23-002562 
23-003760 

DAG69C1 



D Lower 



304-622 



Heat Shield 1 

D Upper 2 

D Lower 1 

D Lower 1 



108 



ORSGSr^AL PAGS JS 
OF POOR QUALITY 



TABLE XXIX - COMPONENT FLIGHT ACCEPTANCE TEST 
Environments and Vehicle Effectivity 



Component 

Electronic Inverter 

Diode Unit 

Poppet Valve Electronics 

Servo Ampl if ier 

Programer 

Intervalometer 

Guidance Unit Assembly 

Rate Gyro Unit 

Power Switching Relay Unit 

Hydraulic Servo Actuator 

Power Control Relay Box 

Radar Beacon 

Radio Command Receiver 

Ignition Relay Assembly 

Ignition Relay Assembly 

Destruct Relay Assembly 

Solenoid Operated Rotary Switch 

FM/FM Transmitter 

Relay Junction Box Transition C 

Resistor Box 

Resistor Box 

Roll & Yaw Compensator 

Body Bending Fi Iter 



Component 


FAT 


Requirements 






Code Number 


(see 


envi ronmen 


tal 


Vehicle 


(see table 


XIX) 


code 


below) 




Effectivi ty 


001 






3 




193 - 207 


002 






3 




/ 


^ 


003 






3 








OOif 






3 








005 






3 








006 






3 








007 






3 








008 






3 








009 






8 








010 






8 








Oil 






3 








012 






5 








013 






5 








01** 






7 








015 






7 








016 






7 








017 






7 








018 






2 








019 






7 








020 






6 








021 






6 








022 






3 




\ 


• 


023 






3 




193 


- 207 



Environmental Test Code : The above components shall be tested to the environments as 

specified below: 

1 Low temperature, temperature shock, temperature-altitude, shock, and vibration. 

2 High temperature, temperature-altitude, shock, and vibration. 

3 Temperature-altitude, temperature shock, and vibration. 
k High temperature, shock, and vibration. 

5 Temperature-altitude, shock, and vibration. 

6 Temperature shock, shock, and vibration. 

7 Shock and vibration. 

8 Vibration. 



109 



PERFORMANCE CRITERIA 

Pre-envi ronmental Tests for each component or subsystem (i.e., test specimen) 
are subjected to a comprehensive evaluation of operating performance character- 
istics under standard conditions and a visual examination. 

Environmental Tests are performed on test specimens in a mode similar to that 
in which it is during the exposure of the component or subsystem to the actual 
environment of flight. 

Post-environmental Tests are always made. The performance evaluation tests 
performed as designated in the preceding paragraphs are repeated and the data 
taken must compare satisfactorily to that previously obtained. The visual 
examination is repeated and an internal examination is performed as practicable. 

FAILURE. CORRECTIVE ACTION, AND RETEST 

Fa i lure - Components or subsystems failing tests are rejected and correc- 
tive action is taken. 

Corrective Act ion - An analysis of the failure is made to determine the 
cause of failure. The failed part analysis consists of a detailed test, 
disassembly, examination, and evaluation of the part. The analysis results in 
identification of deficiencies in the part which could have caused, or did cause, 
the reported malfunction. Repair usually consists of replacing a defective part 
and/or taking quality control measures to prevent recurrence. 

Retest - After the repair of failed components, the component is again 
subjected to the original test requirements. 

SCOUT RELIABILITY INDOCTRINATI ON AND TRAINING 

A Scout Reliability Indoctrination and Training Program has been established 
by the Contractor for the purpose of motivating Scout personnel to provide and 
maintain the desired level of reliability in the Scout system. Fundamentals of 
reliability theory and use of Scout "case histories" are included in the 
training program. 

ROCKET MOTORS 

The solid propel lant rocket motors used on Scout vehicles were purchased through 
the prime contractor, Vought Corporation. The rocket motors are manufactured 
under a quality assurance program utilizing the NASA NHB-5300.4 series quality 
guidelines administered by Vought Corporation. The prime contractor has 
assigned a Quality Control Representative to each motor manufacturer's plant 
for the length of the manufacturing contract. A Vought Rocket Motor Review 
Board recommends action on all major deviations of the NASA/Vought-procured 
motors. A NASA Resident Engineer is chairman of the Vought Motor Review 
Board and a voting member. 



110 



The quality assurance program for the Scout motors is divided into several 
phases. 

(A) The first phase consists of final inspection at the manufacturer's 
plant, acceptance by the prime contractor's representative, and acceptance by 
the designated Government representative. All reported deviations prior to 
shipment of the motors are reviewed by the Vought Propulsion Group and by the 
NASA/SPO Propulsion and Quality Units. The Vought Motor Review Board recormends 
action on all major deviations to the NASA who retains approval rights in such 
instances . 

(B) The second phase of the motor acceptance program consists of a com- 
plete receiving inspection and preassembly inspection at the launch sites. 
Quality requirements are outlined in such manuals as: 

(1) Standard Operating Procedures Volume III - Rocket Motors and 
Pyrotechn ics 

(2) Standard Operating Procedures Volume ill - Field Disposition 
Cr i ter ia 

(3) Manufacturer Testing and Inspection Procedures 

(4) Materials and Specification Lists 

(5) Processing Procedures and Specifications 

(6) Motor Performance Manuals 

(7) Complete Drawings and Documentation Control 

(8) Surveys and Audits 

(9) Quality Control Program Plan (QCPP-0-012) 

ACCURACY 

The accuracy of the Scout vehicle has been continuously investigated and 
improved. The methods used to improve the Scout accuracy are as follows: 

(A) Velocity Meter 

(B) Motor Performance Prediction Study 

(C) Orbital Inclination Study 

(D) Operational Performance and Dispersion Computer Program 

(E) Initial Launching Azimuth Errors 

(F) Error Analysis of the Orbital Results of all the Launches 

(G) Guidance Roll Compensation Study 
(H) Motor Propel lant Studies 

(l) Inertial Guidance Ava i labi 1 ity Investigation 

(j) Azimuth Al inement 

(K) Fourth-stage Attitude Correction and Control System (Figure 62.) 

Completion of the motor performance prediction study (B) indicated motor per- 
formance variations were significantly less than anticipated. Flight with the 
velocity meter developed under the velocity control program (A) confirmed 
the ground motor data and predictions. It was clearly shown that the performance 
of the first three stages was extremely accurate. The fourth-stage impulse was 
less accurate but showed a variability consistent with tunnel test data. 
However, the performance accuracy of the Scout vehicle is still less than 



OF POOR QUALITY 



111 




Q. 
(U 
O 

c 
o 



c 
o 
o 

<u 

CD 

m 



■D 
O 



3 
O 
U 
to 



eg 

^^0 






112 



desired. In view of this, a new comprehensive vehicle error analysis (F) was 
initiated in an effort to clearly identify the major error sources. While the 
motor errors are large, they are not large enough in combination with the other 
evaluated errors to account for the flight performance accuracy level. 

Item (D) , Scout trajectory optimization and linearized pitch computer program 
(TOLIP), obtained from the Lockheed Missile and Space Company under contract 
NASI-5IO6, was designed to perform the trajectory-related calculations nec- 
essary in mission planning and pref 1 ight analysis with a large reduction in 
computer time. It uses a closed-loop steepest descent optimization procedure 
to obtain fl ight trajectories that maximize payload, inertial or aerodynamic 
velocity, or altitude at fourth-stage burnout. Following optimization, the 
pitch program is automatically linearized to enable its mechanization in the 
autopilot system. Control system and body dynamics effects are included in 
the simulation. A large number of constraints on the trajectory and pitch 
program can be included in the optimization and linearization solutions, so 
that a great deal of flexibility as well as recognition of vehicle limitations 
are possible in the use of the program. 

Following the solution for the optimum trajectory and pitch program, the 
computer program can proceed, by option, directly into calculation of: 
(1) radar tracking coordinate histories for up to twenty stations; (2) the 
locus of nominal impact points of the spent stages; (3) nominal dispersion 
envelopes; and (4) failure-mode hard-over turns. Finally, for planning 
purposes, first order performance exchange ratios for several vehicle/motor 
characteristics are calculated. 

Particular attention had been devoted during program development to computing 
speed. The convergence scheme, the general program arrangement, and the sub- 
routines have been selected with this in mind. In some cases, standard sub- 
routines have been modified to provide significant increases in speed for 
special applications. 

IMPROVEMENT 

(A) A stronger Vought Project organization was created. The Vought 
Project organization provided additional Scout-experienced, systems-oriented 
personnel, who had demonstrated specialized technical capability in their 
respective areas, and who would be responsible only to the program. 

(B) a new engineering support contract was initiated. This system's 
engineering contract was started in May 1964 (NASI -4664) . This type of 
contract utilized the strengthened Vought Project organization as the technically 
cognizant group responsible for the total Scout system including rocket motors 
and operations. A more efficient Systems' Management contract was initiated 

in November I968 (NASl-7256). This contract expired in October 1970, and 
similar contracts (NASl-10000, NASl-12500, NASI-I5OOO, and NASl-16200) replaced 
NASl-7256 and the latter is presently in effect. 



113 

(C) Integrated and Streamlined In-plant and Field Operations v;ere part 
of this major improvement. A program for developing standardized procedures 
and configuration control was initially developed in October I963 under the 
Wallops field support contract; and it was further augmented by the systems' 
management contract in conjunction with the initial vehicle recert if ication 
program, whereby all vehicles were returned to the factory and revalidated for 
flight. Table XXX outlines the Quality and Reliability Program. 

The objectives and elements of the standardization program are itemized as 
f o 1 1 ows : 

(A) To maximize reliability and stabilize vehicle operations. 

(1) Deliver a standard flight-ready vehicle with proper documentation. 

(2) Maintain system integrity after delivery. 

(3) Minimize handling, processing, repetitive testing, and human error. 
{k) Apply total experience and training to timely solution of technical 

problems . 

(B) To establish total system capability for sustained increased launch 
rate (two per month per site). 

(C) To improve cost effectiveness by increased reliability. The elements 
of the standardization program are block-standards for vehicles and spares, 
identical equipment at all sites, and an integrated approach to vehicle 
process ing. 

(1) In-plant checks and documentation to assure systems readiness. 

(2) Field checks to monitor deviations in significant measurements. 

(3) Field capability consistent with emergency readjustments. 
(k) Standard Procedures for processing. 

(5) Program surveillance and configuration control. 

Any changes required to SOP's or GSE to complete vehicle processing are submitted 
through the Scout configuration control system for Contractor and Government 
review prior to incorporation. The November 1973 through April 1975 film 
progress report details the procedures for maintaining standardization. The 
Standard Procedures Manuals consist of seven volumes as follows: 

Volume I Administration and Vehicle 

Volume II Ground Support Equipment 

Volume III Rocket Motors and Pyrotechnics 

Volume iV Receiving, Bench, and Transition Tests 

Volume V Vehicle Assembly and Tests 

Volume VI Launch Operations 

Volume VII Countdown 

Figure 63 shows the Standard Operating Procedures as contracted for in 
contract NASI -6935, task order 32. 

(D) a resident representative was established at Vought Corporation, in 
Dallas, Texas. A training and familiarization program was undertaken for 
approximately six months and the resident representative was on site at the 
Contractor's plant in January 1964. He was involved initially in the vehicle 
recertif ication effort. This office was expanded to three residents and 
currently has two residents. This office has proved to be a great asset to 
the Scout Project. 



OF PCORQI-^'^- 
TABLE XXX - SCOUT FIELD QUALITY £- RELIABILITY PROGRAM. 

/yfZP QUAUTT ^ CfLMB/UTr 

CONTROL 

•QCEB-PP-On 

• PURPOSE 

ESTABLISH d.C POLICIES AND PROCEDURES 

• OBJECTIVES 

• MONITORING AND DOCUMENTATION OF ALL TESTING 

• INSURE COMPLIANCE TO SZOMT CRITERIA 

• INSPECTION AND TESTING 

• PROVIDE Ql.C. FIELD LIAISON WITH MSD-T 

•FIELD QUALITY CONTROL MANUAL 

■ DEFINE Q.C. POLICY AND PROCEDURE REQUIREMENTS 

• PROCEDURES 

• CONFIGURATION CONTROL 

• INSPECTION AND CHECKOUT 

• CALIBRATION 

■ NON - CONFORMING MATERIAL 

• DOCUMENTATION 

LIAISON 

• MEETINGS 

FIELD RELIABILITY < QUALITY MEETING 

RELIABILITY ^ ENGINEERING REVIEW MEETING 

PERIODIC FIELD VISITS 

SPECIAL MEETING -INDOCTRINATION * FAMILIARIZATION 

• REVIEWS 

FIELD LOGBOOK REVIEW 
QCTIR REVIEW 
CONFIGURATION CONTROL 

• DOCUMENTATION EXCHANGE 

Bl- MONTHLY REL STATUS REPORT 
VEHICLE END NARRATIVE REPORT 
MALFUNCTION REPORTS 
FAILED PARTS ANALYSIS REPORTS 

• TRAINING AND CERTIFICATION 

ON-THE-JOB TRAINING 
TRAINING AND CERTIFICATION 

•SOLDERING 

•ELECTRICAL CONNECTORS 

•H2O2 SERVICE 

•PNEUMATIC SERVICE 



ORlGfMAL FAGS m 
OF POOR QUALITY 



115 



STANPAm) 0P£J?AT/Af(7 PJ^OCfPaR£S 

(NASI - 6935 TASK ORD ER 32 J 



i^ee 



H GROUND %mm GQPT. 



K ROCKET MTRS. f PYROTEa 



liT REC, BENCH 4 TRANS. 



Y VEHICLE ASSY. ^ TEST 



H LAUNCH OPERATIONS 



START 



N 



IIASA APPROVAL 



n 



y970 



r 



1 

PRINTED 
COPIES 



START 



NASA APPROVAL 



PRINTED 
COPIES 



START 



NASA APPROVAL 



1 



|- PRINTED 
COPIES 



STARTn NASA APPROVAL 



1 



1 



START 



^ 



D 



^PRINTH) COPIES 



t: 



:5 



PRINTED COPIES 



NASA APPROVAL 



Figure 63.- Standard Operating Procedures. 



116 

(E) The NASA ad hoc review conmittee recommendations for improving Scout 
reliability were implemented. 

(1) A reassessment of the Scout environment by study of flight and 
ground records was initiated by independent, formally established contractor 
and Langley Research Center design review committees. A three-month effort by 
the Contractor's design interface review formed the basis for the Langley review. 
Both efforts supplemented an earlier design review conducted by the Contractor 
after the Scout-1l4 ignition system failure. Each penetrated the areas of 
controls, electrical systems, airframe and motor hardware, environment, quality 
and reliability, and structures. Test and acceptance specifications were 
reviewed to establish whether adequate design margins and acceptance criteria 
exist for components as well as systems. 

(2) The ad hoc review committee recommendation to increase vendor 
surveillance was implemented internally by the Contractor. Provisions of the 
NASA (Quality Control 200-series and the Reliability 250-1 series documents were 
added to existing and follow-on contracts. 

(3) Status of the recommendation to deliver a completely checked-out 
vehicle from the factory was discussed above under paragraph (C). 

(F) A Reliability Motivation Program was established. The program adopted 
an awards contract that penetrated to the internal Vought and subcontractor 
project organizations and has proved to be very successful. 

(G) The Scout Evaluation Vehicle (SEV) 

Vehicle S-131R was used to demonstrate and flight-test a group of new 
Scout improvements which included: 

(1) Fourth-stage interchangeabi 1 i ty 

(2) Air-transport demonstration 

(3) Castor MA 

(4) Altair III (FW-4S) 

(5) 75KS spin motors 

(6) Vega beacon 

(7) Autodestruct module 

(8) Dogleg 

(9) Transition "E" 

(10) Ignition monitor 

(11) Electrostatic potential measurement 

This vehicle (the first configuration B) had three independent instrumentation 
systems and a U.S. Army SECOR payload. The flight was a complete success. All 
the new items were incorporated into the standard Scout. 

(H) R&D Improvements 

Vought Corporation contracts NAS1-5592, NAS1-6935, NASl-10000, NASI-IO5OO, 
NASI-I25OO, NASI-I5OOO, and NASI-I5IOO included new research and development 
improvements. Contract NAS1-16200 will include future improvements. 
Table XXXI itemizes many of these improvements. 



117 

The major improvements to the original Scout vehicle are detailed in Table XXX! 
TABLE XXXI - MAJOR R&D IMPROVEMENTS TO ORIGINAL SCOUT (O 



FIRST STAGE 



Algol Pyrogen Igniter 
Improved Algol MB Nozzle 
Composite Material Nozzle 
Modified Jet Vanes and Fin Tips 
Algol IMA Rocket Motor 
Shelf life Extension, Algol IIC Motor 
Single Bridge Apollo Standard Initiator 
New Safe Arm 

New Electrical Connectors 
Factory-sealed Hydraulic System 



THIRD STAGE 



New Light Weight Beacon 

New H2O2 Rel ief Valve 

New Quick Disconnects 

New Safe Ar, 

Modified 2- Pound Motor Valve 

Modified 14- Pound Motor Valve 

Modified ^- Pound Motor Valve 

New T/M Antenna System 

New Power Control Relay Box 

New Head Cap Pressure Transducer 

Improved Rate Gyro 

Modified 37-V Guidance Battery 

New Bearing 

Revised Structure 

Simpl if ied Wir ing 

New Electrical Connectors 

New Command/Destruct Receiver 

New Telemetry System 

60-Pound Reaction Control Motor 

Yaw Torquing 

Redesigned "D" Section 

Redesigned Lower "D" Section for 

S-Band T/M 
Shelf Life Extension for Antares MA 
Roll -Yaw Compensation Unit 
Destruct Receiver Power Switching 
Antares I IB Rocket Motor 

(Used on S-I9I) 
Antares I I |A Rocket Motor 

(Used on S-192) 
Single Bridge Apollo Std. Initiator 



SECOND STAGE 



Castor I lA Rocket Motor 

New H2O2 Rel ief Valve 

New 500- Pound Motor Valve Filter 

New Quick Disconnects 

Modified 40- Pound Motor Valve 

New Safe Arm 

Autodestruct Module 

New Electrical Connectors 

Single Bridge Apol lo Std. Initiator 



FOURTH STAGE 



New Electrical Connectors 

Pay load Separation Timers 

Telemetry/Separation System Module 

Series-25 "E" Section 

Series-200 "E" Section 

Single Bridge Apollo Std. Initiator 

E-G Separation System (not used in 

Phase VI) 
42-inch Diameter Heat Shield 
34- inch Diameter Heat Shield 
Shelf Life Extension, Altair MA 

and I I lA Rocket Motors 



FIFTH STAGE 



Single Bridge Apollo Std. Initiator 
Shelf Life Extension, Alcyone lA 
Rocket Motors 



(1) 



Figures 39 through k2 plus 45 & 46 
illustrate the new motors. 
Figure 64 shows a few of the 
improvements . 



118 

(l) The Office of the Director of the Langley Research Center established 
and authorized the Langley Research Center Scout Program Review Conmittee in 
1972 to make an investigation of and recommendations for the Scout Program to 
assure its continued success. The Committee was composed of an independent 
group of experts from the LaRC Directorates, with membensvfrom Lewis, Goddard, 
Wallops Flight Center, Headquarters, and the Air Force. ' 

At the time the Committee was formed the Scout had 23 consecutive 
successes. The Committee was to recommend actions that would aid the Scout 
Program in achieving 50 consecutive successes.'^' 

The Committee addressed the problems of reliability of existing 
vehicles, reliability of future vehicles, margins of safety as the vehicle is 
modified and upgraded, vehicle systems integration, ground support equipment, 
and technical management. 

The recommendations of the Committee resulted in the following 
act ions : 

(1) Action was taken to insure that the plant, field, and NASA/SPO 
operations contain reasonable numbers of qualified, experienced personnel for 
the life of the program. 

(2) The NASA Resident Engineering and Management Office (REMO) at 
Dallas was strengthened. 

(3) The vendor plant representative system was changed to increase 
visibility during production phases. The function and authority of the rocket 
motor representatives were better defined. 

(k) The environmental storage conditions of the vehicle, such as 
temperature, humidity, shock and handling, were improved. Documentation was 
improved to insure that the health of the vehicle or component in storage is 
known . 

(5) A number of tests and inspections of Scout vehicle, components 
and GSE were changed as a result of the review; such as standardize electrical 
pin retention tests, reduce number of hydrogen peroxide motor hot firings, 
shelf life study of fifth stage (BE-3-A9) rocket motor initiated and the GSE 
maintenance and modification program improved. 

Summary data presented by the Office of Space and Science and Applications 
for all small and medium class launch vehicles indicated that many strings 
of successes had been interrupted in the 20 to 25 range. It was because of 
this cyclic pattern that the committee was proposed. Since the purpose was to 



(^)The committee was designated the Donley Committee and Philip Donley was 

named Chairman. Additional information is available in Vought Report 23-5^8, 

(^^Thirty-seven consecutive successes were achieved setting a World's record. 



119 

prevent the Scout Program from falling victim to this historical cycle, the 
committee had achieved its purpose. Although 37 was less than the goal of 50 
it did set a new World's record and only the Scout S-196 failure interrupted 
the achievement of this goal. To date 8 additional successful launches have 
been added to Scout's historical excellence. 

To achieve the above goal and the five recommendations, the committee included 
in its review the LTV Dallas production facility and management, Langley 
Research Center on-site activities, all launch site activity, organizational 
interfaces, advanced planning, and the general program operations. In addi- 
tion to the previously mentioned actions, the recommendations included the 
spectrum of personnel motivation. 

(J) Scout S-189C, carrying the Netherlands ANS-A satel 1 ite (Fig. 37), launched 
from Vandenberg Air Force Base, California, on August 30, 197^+, at 7:07:^*0 a.m. 
Pacific Time. An elliptical orbit had been attained rather than the near 
circular orbit that had been planned. Langley Research Center, with the con- 
currence of the Space Vehicle Office of the Office of Space Sciences, estab- 
lished a review committee on September 3, 197^, to review and determine the 
cause of the anomaly and to recommend appropriate corrective action. 

(1) Vehicle Anomalies .- Three vehicle anomalies were uncovered 
during the review: 1, the third of ten programed adjustments to the pitch 
attitude rate was absent resulting in an excessive nose-down attitude at the 
end of the third "step" which persisted throughout the remainder of the 
launch trajectory and led to the off-nominal orbit; 2, the "retro" or 
braking thrust was applied to the spent third stage 7.68 seconds later than 
planned - this had no detrimental effect upon the launch but did provide 
evidence as to the cause of the first anomaly; and 3, the roll rate gyro 
malfunctioned during high longitudinal acceleration portions of second- and 
third-stage motor operation. 

(2) Findings . - The committee, after review, analysis, and consid- 
eration of the evidence bearing on the S-189C anomaly concluded: 

(a) The anomalous orbit was caused by the failure of Scout 
to execute the planned pitch rate program during the ascent trajectory. 
Specifically, the third, and only the third, of ten pitch program steps was 
not executed. 

(b) Both the absent pitch program step and the late operation 
of the third-stage "retro" function were probably caused by a partially 
shorted diode. 

(c) The roll rate gyro indicated a fallacious high roll rate 
during periods of high longitudinal acceleration. This anomaly was probably 
caused by the loss of pickcff rotor-to-stator clearance induced by the 
acceleration. 



120 



(3) Recommendations and Responses .- The Scout Project Office 
responses, which were made to the recommendations, are listed below for each 
recommendation. 

(a) Long Term Recommendations - 

-1- The intervalometer diodes should be replaced with a 
modern, proven-type procured from a reliable manufacturer. The use of the 
suspect diodes in other Scout systems should be examined and judgments made 
as to their replacement. 

The Texas Instruments' cell-type diodes (suspect 
type) were replaced by SEMTECH JAN TXV IN645-1 diodes in all systems of the 
hardware presently on hand. The ITT I N6if5 diodes in the available intervalom- 
eters were retained. Action was taken to limit future procurements to the 
use of the SEMTECH diode only, in applications where it is usable. 

-2- Flight acceptance test procedures should be devised 
for checl<ing all intervalometer diodes which might be used in the flight 
profile. Similar test procedures should be devised for checking all diodes 
in flight-critical systems. ^^' 

-3- The intervalometer and the programer should be sub- 
jected to a modified flight acceptance test (workmanship test) after wiring 
of the flight profile. (^^ 

-k- The electronic shop procedures should be reviewed 
to insure that established procedures are being followed. ^^' 

-5- The roll rate gyro screening tests should include 
exposure to a steady longitudinal acceleration with gyro package in proper 
orientation. 

-6- The Scout Project Office should actively participate 
in the response to pertinent GIDEP failure ALERTS. (^^ 

(K) Other Studies and Developments included a fourth-stage attitude 
correction system, evaluation of nondestructive testing techniques for solid 
propel lant rocket motors, evaluation of rocket nozzle materials, trajectory 
reconstruction, and a single point failure analysis of the Scout vehicle. (b^) 

(1) Fourth-Stage Attitude Correction System. - The fourth-stage 
attitude correction system was a requirement for the Scout S-191 pay load. 
The Van Allen (Hawkeye) payload had the requirement of changing the attitude 
of the spinning upper stages of Scout through a preprogramed maneuver after 
fourth-stage burnout and prior to fifth-stage ignition. In order to provide 
this capability a means of controlling the upper stages had to be implemented, 



'^Mll recommendations were accomplished 
'^'Detailed in appendix B. 



121 



The addrtion of an Attitude Correction System (ACS) in tlie fourth stage 
provided this means. The system consisted of the following elements: an 
attitude reference subsystem, a control electronics package, a control sub- 
system, and an electrical power source. All sensors, control electronics 
circuitry, battery, and other electrical/electronic components were integral 
to existing Scout structure and were mounted in a module and on a modified 
fourth-stage T/M ring. The module which contained the sensor (platform) was 
located forward of the fourth-stage motor and beneath the F-transition section, 
The other end components including control subsystem tankage, etc., was 
installed/attached to the modified T/M ring. The weight of the complete ACS 
was approximately 30 pounds exclusive of new structure. 

The development of this capability included the study, design, selection and 
procurement, vehicle integration and testing and storage of a flight-qualified 
system for the Hawkeye mission. The associated activities are noted below. 

(a) Under Task R-6 of Contract NASl-10000 the following activities 
were fjerformed: 

-1- Developed preliminary layout for the location of the ACS 
in the Scout upper stages. 

-2- Developed Math model and computer flow diagram for Scout 
fourth-stage control system study. 

-3- Estimated mass properties for the fourth-stage-at- ignition 
and burnout for this mission. 

-k- Defined the modification to the NEMAR program to provide 
the capability for simulating the ACS. 

-5- Defined the loads and dynamics considerations; fourth 
stage pointing errors, expected fifth-stage tip-off; maximum expected fifth- 
stage coning, expected boost vibration environment for the ACS, axial and 
torsional bending modes for the fourth stage with the Hawkeye spacecraft, 
and effects of body flexibility on the motion at the ACS sensor location. 

-6- Developed two digital computer routines for simulating 
spinning body control. 

-7- Conducted mission accuracy analysis. 

-8- Developed overall preliminary requirements for the ACS. 

(b) Under Task Order No. 3 of Contract NAS1-10500 the following 
activity was performed: 

-1- Developed final ACS requirements. 

-2- Procured one set of ACS hardware. 

-3- Conducted mission thermal analysis to define thermal 
control for the T/M, ACS, and RCS systems. 

-k- Electrically and structurally modified the Scout upper 
stages, and installed the ACS. 

-5- Performed modifications to the computer program to accept 
the selected vendor math model, and performed fourth-stage accuracy analysis 
and a mission accuracy analysis. 

-6- Fabricated portable suitcase- type test equipment and 
associated cables required to support testing. 



OF POOR QUftLlTii 



122 



-7- Conducted ACS bench tests, and simulated flight 
acceptance tests including temperature-altitude, shocl< and vibration. 

-8- Conducted systems and final acceptance tests with 
the ACS installed in flight sections. 

-9- Disassembled flight hardware and placed in Government 
Bonded Stores. 

-10- Specified mission reorientation angle and calibrated 
the system to provide the angle. 

-11- Supported as necessary a Government design review 
to review the detail design and installation concepts. 

(c) Under Task R-62 of Contract NAS1-10000 the following 
activity was performed: 

-1- Removed existing fifth-stage telesponder components 
from GFE supplied fifth-stage hardware. 

-2- Installed the ACS performance telemetry components 
in the GFE fifth stage (F-Section). 

-3- Removed existing GFE F-Section despin system. 

-k- Modified existing fifth-stage wiring for payload 
interface and telemetry and ignition requirements. 

-5- Evaluated the fifth-stage modifications to determine 

the effects upon balance and weight distribution. 

Figure Sk shows the detail schedule for the fourth-stage ACS. 







1973 




STATUS 


J 


F 


M 


A 


M 


J 


J 


A 


S 





. CONTRACT GO-AHEAD 


REC'VD MARCH 1972 






















• ESTABLISH SYSTHl RBJUIRIMENTS 


CCMP APRIL 1972 






















• ACS & TANK PRCCUKlMEMr 






'Hi 


















. CONDUCT THERMAL ANALYSIS 


CCMP AUG 1972 






















• VEHICLE HARDWARE: 
























STRUCTURAL MODS 




-X 






-Y 




-X 










ELECTRICAL MODS 


Y— 






FLIGHT UNIT ASSEMBLY 










SYSTEM EVALUATION 


CCMP SEPT 1972 


















Y 




. TESTING 
















• GFE STORAGE 




















X 




• DETERMINE REORIENTATION ANGLE 


CCMP DEC 1972 






















• DESIGN REVIEW SUPPORT 






















X 


. FINAL REPORT 




















X 





Figure 6k.- Detail Schedule - Fourth-Stage ACS 



123 

(2) Solid Rocket Motor Nondestructive Testing Study .- Under contract 
NASI-899^ a study to review the advanced rocket motor NDT inspection techniques 
then in use was conducted. The purpose of this study was directed at maintain- 
ing and improving the high reliability of the Scout rocket motors. The results 
of the study indicated a need to perform an additional detailed investigation 
of certain advanced techniques to determine their applicability and effective- 
ness on Scout motors. Contract NASI -11 867 was funded for that purpose. 

The study was conducted by the General Electric Company of Philadelphia, 
Pennsylvania. The primary effort included the investigation of such techniques 
as filmless automatic bonding inspection system (FABIS), acoustic resonance 
and improved magnetic particle penetrometer, ultrasonics, and radiography 
techniques. In addition, the study determined the value of constructing a 
centralized NDT facility which would house the recommended test equipment and 
which would provide inspection for all motors used on the Scout program. 

(3) Evaluation of Rocket Nozzle Materials .- Material studies have 
indicated that solid rocket nozzle throat inserts made of certain ceramic 
materials should have an advantage in thermal shock resistance and erosion 
over graphite billets and ablatives used in Scout motors. The objective of 
this effort was to determine whether these potential advantages could be 
realized in a practical Scout motor upgraded nozzle in the various motor 
stages. This would eliminate two disadvantages of Scout throat inserts being 
used at the time, (a) the inherent uncertainty in graphite billet properties 
and (b) the nozzle performance inefficiency associated with ablating throats. 

Techniques for hot pressing small scale rocket nozzle inserts have been 
developed. Small scale inserts have been fabricated from the hafnium oxide- 
tungsten-rhenium fiber composition which has demonstrated the best thermal 
shock resistance in earlier studies. Inserts were tested in small scale solid 
propel lant rocket motor firings at Hercules Incorporated, Allegany Ballistics 
Laboratory. The erosion and thermal shock characteristics of the composite 
insert were evaluated in the motor firings. Analytical and experimental 
investigations were broadened to study the ceramic-metal fiber interface and 
the thermal shock characteristics of the material on the microstructural level. 
Theories relating the measured microscopic properties to crack sizes and crack 
densities were developed. Successful functioning of the inserts in the motor 
tests led to consideration of incorporating them into a fourth-stage Scout 
nozzle for further motor testing. The evaluation was performed by N.C. State 
and completed July 197^- 

(^) Trajectory Reconstruction .- The Scout trajectory reconstruction 
program, SPEAR (Scout performance ^valuation and Ascent R^econst ruction) was 
developed for the Scout Project Office, Langley Research Center by Lockheed 
Missiles and Space Company. Instructions for the utilization of SPEAR are con- 
tained in two manuals, LMSC/D030984 "User's Manual - SPEAR" and LMSC/DO30985 
"Programmer's Manual - SPEAR." These were provided as fulfillment of Part 
V.A.2 of the NASA contract NASl-9204. 

The SPEAR program was designed to reconstruct a Scout vehicle trajectory for 
postf 1 ight analysis. The program consisted of three phases: Phase 1 was to 



124 



obtain the best estimate of a Scout trajectory; phase 2 was to obtain the 
best estimate of Scout vehicle characteristics (thrust, weight, aerodynamics, 
etc.); snd phase 3 was to obtain the best estimate of the trajectory and 
vehicle parameters for spin-stabilized stages. 

The work was conducted under the direction of the Scout Project Office. 
Technical monitor for the initial period of development was Donald G. Eide. 
This responsibility was assumed by Joseph W. Drewry for the latter period of 
the contract. 

The SPEAR computer program is a Scout trajectory reconstruction program for 
use on the NASA Langley Research Center CDC 6400/6600 computing system. The 
basic fitting technique employed had been developed by Loclcheed Missiles and 
Space Company (LMSC) and existed in operational postf light programs for its 
in-house activities. The corresponding programming for this application 
required only the modifications to insure compatibility with the specifica- 
tions of the Langley CDC 6400/6600 system. The contract work concerned 
primarily the mathematical simulation of the Scout vehicle, the derivation 
of the partial derivatives required in the fitting process, and the implemen- 
tation of the theoretical development into a computer program operational at 
the Langley Research Center. 

Included under contract scope was the development of necessary data condition- 
ing functions. It was early recognized that these capabilities would best 
be provided as auxiliary programs to avoid additional complexities in the 
main analysis program. Documentation of the data conditioning programs was 
included in the contract report. 

Development was performed on a UNIVAC 1108 computer in the LMSC Central Com- 
puting Facility. Program design and coding stressed independence of computing 
machine and observed the specifications supplied by NASA for the Langley 
CDC 6400/6600 system. A similar, though not identical, system at a Control 
Data Corporation Data Center was used for final checkout prior to installation 
of the programs on the Langley computing system dated Feburary 1, 1971- 

The end product was a powerful tool for determining trajectories and analyzing 
the Scout vehicle performance. The main program has the code name SPEAR. The 
trajectory reconstruction is a general capability for any vehicle for which 
triaxial accelerometer and body attitude rate data are available. The per- 
formance evaluation capability was restricted to vehicles with propulsion and 
control systems similar to those modeled for the Scout vehicle. The first of 
the auxiliary programs is SPFLTR (SPEAR Filter) and provides data conditioning 
(including wild point rejection, data replacement, data synchronization, 
smoothing and differentiating) for any data tape with up to 30 variables per 
time point. The second is TPGEN (Tape processor and Gen erator) , reflecting 
its use in processing data tapes and generating tapes in the standard format 
expected by SPEAR. The third is PL0T2O, the output of which is input to the 
CalComp plotter. 



125 



(a) Theoretical Development .- The basis for computer program 
SPEAR was the Kalman filter. This technique as applied to the extraction of 
information for discrete measurements contaminated by random errors has 
proved very successful in the reconstruction of powered ascent trajectories 
and the evaluation of vehicle performance. In SPEAR, the two main problems 
of trajectory reconstruction and performance evaluation are solved in sequence. 
In phase 1 the launch trajectory is fit to the radar. The best estimate 
trajectory obtained from phase 1 is then input data for phase 2 in which the 
vehicle performance is evaluated. The Kalman technique is applied in both 
phases . 

The follbwing is a somewhat idealized but accurate motivation for using the 
Kalman filtering technique for postflight analysis. 



m 



The design of a missile usually starts with the definition of a mission, the 
mission being specified by injection or orbit parameters with their desired 
tolerances. A design team is called upon to translate these objectives into 
hardware design parameters and their allowed tolerances. A pref light error 
analysis is performed to check the compatibility of the hardware design with 
the m iss ion. 

The manufacturing group uses the design specifications and builds the hardware. 
At this time the hardware parameters become statistical random variables with 
means and variances. Quality control is employed to insure that the statistics 
of these parameters are compatible wi th the design specifications. 

The pref light knowledge at this point is not the actual hardware values but a 
measure of their statistics. When the vehicle is launched, telemetry is em- 
ployed to monitor vehicle hardware performance and radar is employed to 
monitor vehicle trajectory performance. 

The postflight team must ascertain whether the actual vehicle hardware and 
mission parameters were within tolerance. The team begins by reconstructing 
the trajectory and encounters the first obstacle. It becomes clear that all 
the data sources are statistical random variables with means and variances 
(the vehicle hardware parameters by virtue of manufacturing techniques and 
the telemetry and radar data by virtue of communication equipment noise and 
other random disturbances). The data reduction personnel are called upon to 
supply the uncertainties of the telemetry and radar data. At this point one 
could say that the most likely values of the parameters would be the smoothed 
value obtained from the noisy data. A closer analysis would reveal that con- 
flicts arise in this fashion. The following question would be asked - What 
is the "size" of the uncertainty on motor head cap pressure relative to the 
"size" of uncertainty on radar range azimuth and elevation? The analyst 
must answer these types of questions before selecting the most accurate 
source for a particular parameter. But even by doing this he is ignoring 
some information (even though less accurate) that should contribute, to a 
lesser extent, to the value of the parameter. 

At this point the postflight group was confronted by two main questions. 
First, how can one compare all the data sources with their assigned 



126 



uncertainties? Second, what was the most likely value of these parameters 
and to what accuracy, given all the data? It is within this setting that the 
Kalman fitting problem was posed. The first question was answered by the 
definition of a model and the second by use of Kalman's fitting equations. 

(b) Role of the model .- As hinted above, the purpose of the 
model was to provide a method of comparing all the data sources to be used 
and their respective variances. The demands on the model are that there 
must be fitting parameters which can be adjusted to explain the discrepancies 
between the various data sources except for those caused by random noise. 



127 



CHAPTER VI - SCOUT PROCUREMENT PROGRAM 



128 

In May 1958 contract L-55931 (G) was awarded Thiokol Corporation for second 
stage Castor motors. In April 1959 contract NASI -2^9 was the first Scout 
contract awarded to Chance Vought Corporation^' ) . The procurement require- 
ments for Scout expanded as shown in publication LWP-80U, pages 253 through 
256, and publication TM X- 72628, pages 313 through 3I6, which included 1U years 
through 1971 . 

The Scout contracts include the following hardware, systems, and software of 
the Scout program: vehicle procurement, motor procurement, spares procurement, 
systems management, launch site requirements, research and development, launch 
services, and anomalies and failure investigations. 

Each of the above was contracted for in each phase of the Scout program. 
Table XXXII details the quantity of vehicles funded, contracted, and launched 
through Phase VI. It shows the number of vehicles by agency and fiscal year 
funds. Figure 65 illustrates a typical Scout Systems Management contract and 
shows NAS1-10000 which started during Phase V and ended November 1973 during 
Phase VI. Transition from one contract to another for Scout systems management 
was always accomplished very smoothly. The Prime Contractor and NASA worked 
diligently together to accomplish excellent and economical transitions in each 
phase and contract. 

Table XXXIII lists the major contracts, specifies the phase they cover, and 
designates the type of contract and the contractor. It also lists the planned 
follow-on contracts. NASA publication LWP-804 itemizes 13^ contracts through 
FY 1965, and TM X-72628 itemizes 51 contracts through November 1971. Table 
XXXIV(a) itemizes an additional kS contracts through I979. The contracts 
designated with an asterisk are detailed in subsequent pages. Scout Phase VII 
hardware procurement and manufacturing period coincides with the Scout Phase VI 
assembly and launch period, therefore any Phase VII contracts prior to Decem- 
ber 1979 are also listed. Prior contracts that include Phase VI hardware or 
software are listed in table XXXiV(b). A historical layout of the Scout contracts 
for the Scout program is shown in figure 66. The Langley Research Center was 
responsible for all Scout contracts. Table XXXIII shows which contracts were 
firm fixed price (FFP), fixed price incentive (FPl), and all the other types 
as designated. Phase VI management contract (NASI -10000) was fixed price 
incentive/award research development (FPIA) with special cost-reimbursable 
(CPFF) and fixed price (FFP) provisions. Phase VI was extended to contract 
NASI-I25OO which was similar to NASl-10000 in structure. Many other contracts 
involved aspects of the Phase VI program including NASl-7256 and NASl-15000. 
However, NAS1-7199, NASl-10000, and NASl-12500 contracts constitute most of the 
effort for Phase VI. All Scout contracts were technically monitored by the 
LaRC Scout Project Office. The Prime Contractor, Vought Corporation (formerly 
LTVAC/Vought Systems Division) was contractually responsible for all Scout 
systems and hardware. A typical polar orbit with an international payload (UK-4) 
is shown in figure 67 (vehicle S-I83). 



(^^The Contractor made several name changes during the Scout Program from 
Chance Vought Corporation, such as Ling-Temco-Vought , LTV Aerospace, 
LTV Missiles and Space, LTV Aeronautics, LTV Systems Division, and at 
present and henceforward Vought Corporation. 

(^^"User" refers to the spacecraft owner. 



129 



ORIGINAL PAQ^ [^ 
OF POOR QUALITY 



TABLE XXXII - SCOUT VEHICLE PROCUREMENTS (Phases I through VI) 

OTHERS 
FY (AEC) (ESRO) 

FUNDED NASA NAVY AIR FORCE (UK)(AEROS) TOTAL 

Phase I (Dev.) 9 9 

Phase II (FY62) 3 $(1) 2 10 

Phase III (Recertified) 

(FY62) 2^^^ 11 Ok 

(FY63) 3 1 4 

(FY64) 5 5 

(SEV) _1 _2 

Phase I I I Total 111 1 1 14 

Phase IV (FY62) 3 2 5 

(Incentive) (FY63) 10 1 

(FY64) 12 2 5 

(FY65) Oil 2 

(FY66) 4 11 6 

(FY67) 12 3 

(FY69) 10 1 

(FY70) _2 2 

Phase IV Total 10 9 6 25 

Phase V (Fixed Price, Award) 

(FY67) 3 10 4 

(FY68) 3 3 

(FY69) 2 2 

(FY70) 2 1 3 

(FY71) 2 2 

(FY72) 

(FY73) _L 2 £ J. 

Phase V Total 13 1 1 Ts 

Phase VI (Fixed Price, Award) 

(FY67) 3 3 

(FY68) 

(FY 70) 

(FY72) 2 2 

(FY73) 3 2 5 

(FY74) 2 1 3 

(FY75) 

(FY76) 1 1 

(FY79) L 2. 1 1 _1 

Phase VI Total 8 3 1 3 T5 

Special A.F.(3) fy62) 4 4 

TOTAL 54 19 14 5 92 (^) 

■ 'One AEC with Navy-supplied Scout - 

(^)Recertif icat ion. 

(3)Direct D.O.D. procurement from LTV (not NASA Scouts). 

(^)|n addition to the 92 Scouts through Phase VI, 10 Phase VII Scouts were 
launched prior to the last Phase VI launch. 



130 



ORIGINAL PASS \S 
OF POOR QUALITY 




o 
o 
o 
o 



o 

ID 



c 
o 
o 



c 

0) 

E 

ID 

c 

ID 

3: 



3 

o 
o 



in 



o 0~\oor^vD LA-T r^c^' — o IT>00 r-^vo ltv^t cocm 

rOCNlCMCMrsir>JCSJC>4CSICMCNl' — ■ — • — • — • — ^~ • — • — 



I ' I I I I I I 
OCr\oOt-^vOLr\J-iv-icM — 



sNomiw - s«vnoa 



131 



TABLE XXXIII - SUMMARY OF SCOUT CONTRACTS 



'• VEHICLE PROCUREMENT 



Phase 1 


NASI -249 & 


Phase 1 1 


NAS 1-1295 


Phase 1 1 & IV 


NAS 1-1295 S 


Phase IV 


NAS 1-2650 


Phase V 


NAS 1-56 10 


Phase VI 


NAS 1-7199 


Phase VII 


NAS 1-1 1000 


Phase VIII 


NASI -15000 


MOTOR PROCUREMENT 


Phase 1 


NAS5-53 




L55931 




S-IOIOG 




S-IOOG 


Phase II & III 


NASI-I33O 


Phase 1 1 


L93419 


Phase II 


L93985 


Phase 1 II 


L2061 




LO3829 




NAS 1-3664 


Phase IV 


NAS 1-3822 




NAS 1-5034 




NAS 1-3493 




NAS 1-3698 




NAS 1-5883 


Phase V 


NAS 1-5610 


Phase VI 


NAS 1-7199 




NAS 1-6935-40 


VI,V.||,VIII 


NAS 1-9258 


Phase VI 1 


NAS 1-1 1400 



NAS 1 -900 



NAS 1-3589 



NASl-13100 
Phase VI l,VI I I NASI -14200 

3. SYSTEMS MANAGEMENT 



Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 



V 



III 
IV 

IV & 
V 

V £. VI 

VI & VI I 
VI I ,VIII 
VI I.VIII 



NAS 1-3657 
NAS 1 -4664 
NAS 1-6020 
NAS 1-7256 
NAS 1-10000 
NAS 1-12500 
NASI -15000, 
NASI -16200 



CONTRACTO R 

LTV 

LTV 
LTV 
LTV 
LTV 
LTV 
LTV 
LTV 



OR TYPE 

FFP & 

CPFF 

CPFF 

CPFF 

FPI 

FFP 

FFP 

FFP 

FP 



First Stage (Algol I) 
Second Stage (Castor I) 
Third Stage (X-254) 
Fourth Stage (X-248) 
First Stage (Algol I & I I ) 
Second Stage (Castor I) 
Third & Fourth Stages (X-248) 
(and X-259) 

Second Stage (Castor I) 
Third Stage (X-259) 
Fourth Stage (X-258) 
First Stage (Algol II) 
Second Stage (Castor II) 
Third Stage (X-2 59) 
Fourth Stage (X-258) 
Second, Third, & Fourth 

Stages (Castor, X-258, X-259 

and FW4S) 
All Motors 
Four Stages (Algol II, 

Castor II , X-259, FW4S) 
Algol I IB Nozzles 
First Stage (Algol I I I) 
Castor I lA, Antares I I , 

and Altair MIA 
Algol III. 

Second, Third, & Fourth 
Stages 



Aerojet 


CPFF 


Thiokol 


CPFF 


ABL 


CPFF 


ABL 


CPFF 


Aerojet 


CPFF 


Thiokol 


CPFF 


ABL 


CPFF 


Thiokol 


CPFF 


ABL 


CPFF 


ABL 


CPFF 


Aerojet 


FFP 


Thiokol 


FFP 


Hercules 


CPFF 


Hercules 


FFP 


LTV 


FFP 


LTV 


FFP 


LTV 


FFP 


LTV 


FP 


LTV 


FFP 


LTV 


FFP 


LTV 


FP 


LTV 


FP 



NAS1-15100 



LTV 


CPFF 


LTV 


CPIF 


LTV 


FPI 


LTV 


FPIA 


LTV 


FPIA 


LTV 


FPIA 


LTV 


FPIA 


LTV 


FPIA & CPFF 



132 



TABLE XXXIII - SUMMARY OF SCOUT CONTRACTS Continued 



SPARES 



FY 1963 


NASI -1970 


FY ^^ek 


NASI -3^20 


FY 1965-66 


NASI -^664 


FY 1967-68 


NASI -6020 


FY 1969-70 


NASI -7256 


FY 1971-73 


NASI -10000 


FY 1973-76 


NASI-I25OO 


FY 1977-79 


NAS1-15100 


FY 1979-81 


NASI-I5OOO 


FY 1981- 


NASI -16200 


LAUNCH SITES 




East Coast 


NASl-2ii55 


West Coast 


NASl-1^1 


Africa 


NASI -^99, W 




NASI-I5IOO-J, 


RESEARCH AND 


DEVELOPMENT 


FY 1959 


NASI -249 


FY 1961 


NASI-I33O 


FY 1963 


L- 15993 


FY 1959 


NORD ^SSko 


FY 1962-63 


NASI -1928 


FY 196i+-65 


NASI -3899 


Phase 1 1 1 


NASI -4794 


FY 1965 


NASI -4793 


FY 1965-66 


NASI -4795 


FY 196it-65 


NASI-5IO6 


FY 1966-67 


NASI -6692 


FY 1968-70 


NASI -6868 


FY 1967 


NASI -6935 


FY 1967 


NASI -6935-5 


FY 1967 


NAS1-6935-10 


FY 1967 


NASI -6935-34 


FY 1967 


NASI -6935-41 


FY 1967 


NASI -6935-44 


FY 1967 


NASI -6969 


FY 1967-69 


NASI-7IO2 


FY 1969 


NASI -8541 


FY 1969 


NASI -8994 


FY 1969-70 


NASI -9204 


FY 1969-7^ 


NASI -9258 



CONTKACTOR 



LTV 
LTV 
LTV 
LTV 
LTV 
LTV 
LTV 
LTV 
LTV 
LTV 



Original Scout Development 

First Stage Motor (Algol II) 

Second Stg .Motor (Castor II) 

Third & Fourth Stages 

(X-259 and X-258) 

Product Improvement 

Product Improvement 

Algol Studies 

Castor Studies 

X-258 and X-259 Studies 

Studies - TOLIP 

Product Improvement 

Fifth Stage 

Product Improvement 

Roll Yaw 
■13 S-Band 
Jet Vane Studies 
Larger Heat Shield 
Fourth Stage S-Band 
Studies - Error Analysis 
Fifth Stage Motor (BE-3) 
Studies, Instrument Response 
N.D.T.T. 
Studies - SPEAR 
ALGOL I I I - First Stage 



FPIA 
FPIA 



TYPE 

CPFF 

CPFF 

FFP 

FFP 

FP 

FP 

FP 

CPAF 

& CPFF 

& CPFF 



LTV 
LTV 
LTV (Italy) 



CPFF 
CPFF 
FP.CPFF 



LTV 


FFP 


Aerojet 


CPFF 


Thiokol 


CPFF 


Hercules 


CPFF 


LTV 


CPFF 


LTV 


CPFF 


Aerojet 


FFP 


Thiokol 


FFP 


Hercules 


FFP 


Lockheed 


FFP 


LTV 


CPIF 


LTV 


CPIF 


LTV 


CPIF, 




FPI, FP.CPFF 


LTV 


FFP 


LTV 


CPFF 


LTV 


FFP 


LTV 


CPIF 


LTV 


CPIF 


TRW 


FFP 


Hercules 


FFP 


AVCO 


CPFF 


GE 


CPFF 


Lockheed 


FFP 


LTV 


FFP 



133 



TABLE XXXIII - SUMMARY OF SCOUT CONTRACTS Concluded 
6. RESEARCH A ND DEVELOPMENT Continued CONTRACTOR TYPE 



Phase 
Phase 
Phase 
Phase 
Phase 



& VI 



FY 1971-72 



NASI -10000- 
NAS1 -10481 
NASI -10482 
NASI -10483 
NASI -10484 

NASl-10500 



Smal 1 Product 
X-258 Studies 
Castor Studies 
X-259 Studies 
Algol III and 

and Improvements 
Product Improvements 



Improvements 


LTV 


CPFF 




Hercules/B 


CPFF 




Thiokol 


CPFF 




Hercules/B 


CPFF 


FW4S Studies 


UTC 


CPFF 



Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 



I NASI-IO504 Improved Guidance Study 
S-VII NASI-I25OO-R Product Improvements 
I &V1II NASI-I5IOO-R Product Improvements 



I NAS1-14619 

II NASI-I45OO 

& VI I I NASI -15000 
II NASI -15423 

I £• VI I I NASI -15650 



Algol I I I Study 
Guidance Development 

Product Improvements 
Antares I I I Study 

Third-Stage Nozzle 



LTV 



LTV CPFF, 

CPIF.FPI.FP 
Martin Marietta FP 
LTV CPFF 

LTV CPAF 

UTC CPFF 

(Teledyne) CPFF 

LTV CPFF 

SAI CPFF 

SAI CPFF 



LAUNCH SERVICES 



Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 



I NASI -900 

II NASI -1295 

III NASI -21 89 

III NASl-3615 

IV NASI -4664 

IV S. V NASI -6020 

V NASI -7256 

V & VI NASI -10000 

VI £. VI I NASI-I25OO (11 

VII NASI-I5OOO (11-1 



thru February 1, 1964 
thru October 1 , I965 
(7-1-66 thru 11-1-66) 
(11-1-66 thru 11-1-68) 
(11-1-68 thru 11-1-70) 
(11-1-70 thru 11-1-73) 

1-73 thru 11-1-76) 
76 thru 11-1-81) 



VII &VIII NASI-I62OO (Effective II-I-8I) 



LTV 


CPFF 


LTV 


CPFF 


LTV 


CPFF 


LTV 


CPFF 


LTV 


CPIF 


LTV 


FPI 


LTV 


FPIA 


LTV 


FPIA 


LTV 


FPIA 


LTV 


FPIA 


LTV 


FPIA, CPFF 



8. RANGE OPERATIONS 



Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 



V 

V 

VI 

VI 

VI 

VI 

VI i 

VI i 

VI I 

VI I 

VI 

VI I 

VI I 

VII 

VI I 
11 1 I 

V I I 

VI I 
VI I 
VII 
VI I 
VI i 
VI I 
VI I 
VI I 



VI I 
VII 



FY71 Operations & Maintenance 
FY72 Operations & Maintenance 
FY75 Operations & Maintenance 
FY73 Operations £■ Ma intenance 
AEROS & ANS (FY75 Ops.SMaint.) 
OUINTRON (FY76 Comm., Ops.&Mt.) 
L-5O98A FY75 Communications, Ops, & Main 
L-29075A FY75 Range Services 
2238 7A FY 76 Sr 7T Com., Ops. & Ma int. 

FY76 Launch Services DAD/S-I96 

Fac. Mod. &Refurb, Stearns-Rog. 

UK-X4 Range Costs, S-188 

FY77 VAFB Util ities Costs 

FY7T Range Services, S-197 

FY77 Connmuni cat ions, Ops.,& Main 

FY77 Range Services, S-200 

FY78 Range Services for NASA 

FY78 Range Services, S-201 

FY78 VAFB Util ities 

FY78 Communications, Ops. & Main 

FY79-82 Range Services 

FY79-80 Scout Range Services 

Range Services for MAGSAT 

Mod. Spin Balance Machine, VAFB 



■52073 

■64709 

■24697A 

■75052 

■793OA 

-88316 



-27381A 

-29062A 

-4616a 

•5072 5A 

■50692A 

-52306A 

-68201A 
-68202A 
-68209A 
-691 48A 
-68200A 
-86492A 
-86493A 
-93196 



MPE 



SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov' t 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


.) SAMTEC 


Gov' t 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov' t 


SAMSO 


Gov't 


SAMTEC 


Gov't 


4392 ATG 


Gov't 


SAMTEC 


Gov' t 


t . SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


t. SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMTEC 


Gov't 


SAMSO 


Gov' t 



nk 



TABLE XXXIV(a)- SUMMARY OF SCOUT CONTRACTS (1972-1979) 



Contract 










Date 


Contract Number 
NASI -11 400 


Contractor 

LTV Aerospace Corporation (HTC) $ 


3 


Amount 


>-Mar 1 


972 


,611,860 


Mar 1 


972 


L-55240 


U.S. Army Munitions Command 




92,000 


May 1 


972 


NASI -11 000 


LTV Aerospace Corp. - Phase VI 1 


10,488,925 


Jul 1 


972 


L- 75052 


USAF (SAMTEC) 




11,500 


Sep 1 


972 


NAS1-11867 


General Electric Company 




173,363 


Nov 1 


972 


NASI -11 859 


Thiokol Chemical Corporation 




145,302 


Nov 


972 


NASI -11972 


Scientific Atlanta 




245,500 


Mar 1 


973 


L-88316 


USAF (SAMTEC) 




127,844 


Apr 1 


973 


NAS1-10172 


LTV-Custodian of Govt. Property 







Jun 


973 


L-84253 


U.S. Navy Ammunition Depot 




42,968 


Jun 1 


973 


L-93196 


AF-WTR Spin Facil ity 




100,000 


>-Nov 1 


973 


NASI -12500 


LTV-Systems Mgt . (1 1-1 -72/1 1 -1 -76) 


30 


,125,802 


Dec 1 


973 


L- 12904 


A.F. Rkt. Prop. Lab-Fire 2 Altair II 


' s 


40,000 


Apr 1 


974 


L- 5908a 


USAF (SAMTEC) 




147,154 


Jun 1 


974 


L-7930A 


USAF (SAMTEC) 




692,282 


-Sep 1 


974 


NAS1-13100 


VC - Algol 1 1 1 Motors (HTC) 


3 


,849.245 


Mar 1 


975 


L-22387A 


USAF (SAMTEC) 




75,000 


Apr 1 


975 


L-24697A 


USAF (SAMTEC) 




779,465 


May 


975 


L-27381A 


USAF (SAMTEC) 




124,815 


•-Jul 1 


975 


NASI -14200 


VC - Phase VII £• V 1 1 1 Mtrs.,S-192 


10 


,635,981 


Oct 


975 


L-29062A 


USAF (SAMSO) 




425,000 


Nov 


975 


L-29075A 


USAF (SAMTEC) 




170,154 


May 


976 


NASI -14388 


VC - Igniters (3rd Stage) 




183,656 


Sep 


976 


L-4616A 


USAF (SAMTEC) 




829,897 


Sep 


976 


L-50692A 


USAF (SAMTEC) 




31 ,800 


Oct 


976 


L-50696A 


USAF (SAMTEC) 




102,500 


Oct 


976 


L-51743A 


U.S. Energy Res. & Dev . Admin. 




25,200 


Oct 


1976 


L- 52306a 


USAF (SAMTEC) 




70,526 


Oct 


1976 


NASI -1461 9 


UTC - Algol 1 1 1 




299.372 


-Nov 


1976 


NAS1-15000 


VC - Systems Mgt. (1976-1982) 


62,247,425 


Nov 


1976 


NASI -151 00 


VC - Systems Technical Support 


13 


,657,211 


Feb 


1977 


NASI -14500 


VC - Advanced Guidance Sys. Dev. 


4 


,046,237 


Apr 


1977 


L-507IOA 


AEDC - Test Fire Star-30 Motors 




53,320 


Jun 


1977 


L-50725A 


USAF - VAFB Utilities, Scout, FY77 


7,500 


Jul 


1977 


L-507OOA 


Science Applications - Army Analyt 
ical Support, Antares IMA 


_■■ 


50,000 


Aug 


1977 


L-50723A 


San Marco Invoices, Payment 




8,322 


Aug 


1977 


L-50726A 


Motor Storage at NAD 




60,000 


Aug 


1977 


L-68202A 


USAF (SAMTEC) - Range Services 




89. 553 


Aug 


1977 


NAS1-14950(F) 


LTV Revised FY78 Equipment Contract 





Sep 


1977 


L-68200A 


USAF (SAMTEC) - Range Services 




715.300 


Oct 


1977 


L-69148A 


USAF (SAMTEC) - Quintron 




77.500 


Nov 


1977 


L-682OIA 


USAF (SAMTEC) - Range Services 




30,905 


Dec 


1977 


L-68209A 


USAF - VAFB Utilities, Scout, FY78 


11.553 


Jan 


1978 


NASI -15220 


Ellis & Watts - WFC & WTR A/C Uni 


ts 


133.445 


Nov 


1978 


L-68203A 


U.S. Army - Motor Storage (HAAP) 




118.471 


Dec 


1978 


L-68208A 


U.S. Army - Add. Mag. Mod. (HAAP) 




84,963 


Dec 


1978 


NASI -15650 


SAI - Scout Motor Support 




240,840 


Jul 


1979 


L-86492A 


USAF - VAFB Range Services (I98O) 




59.755 


Oct 


1978 


L-86493A 


USAF - VAFB MAGSAT Range Services 




174.152 


Dec 


1979 


L_86494A 


USAF - VAFB Utilities, FY1 979-80 




159,500 



•■-Itemized elsewhere. 



135 



TABLE XXX IV (b)- 



SUMMARY OF SCOUT CONTRACTS 
(Prior to 1972) 



INCLUDED IN PHASE VI 



Contract 
Date 



Mug 

"Nov 

Jan 

May 

May 

*Apr 

"Dec 

~'-Jun 

"Nov 

'-"Dec 

'-"Dec 

wVjan 

;-v,-Feb 

w.-Mar 



1966 

1966 

1967 

1967 

1967 

1968 

1968 

1969 

1970 

1970 

1970 

1971 

1971 

1971 



Contract Number 

NASI -5610 
NASI -6020 

NASI -6935 
NASI -6868 
NASI -71 02 
NAS1-7199 
NASI -7256 
NASI -9258 
NASI -10000 
NASI -10481 
NASI -10483 
NASI -10482 
NASI -10484 
NASI -10500 



Contractor 

LTV 

LTV 

LTV 

LTV 

Hercules 

LTV 

LTV 

LTV 

LTV 

HI/ABL, Tech. Support-X258 Mtrs. 

Hi/Bacchus, Ditto to X259 Mtrs. 

TCC, Ditto to Castor Motors 

UTC, Ditto to Algols and FV4S 

LTV 



Amount 

$12,343,833 

13,489,722 

5,048,879 

1,181,519 

528,525 

13,168,748 

12,781,000 

4,426,568 

28,167,005 

320,794 

351,050 

201,669 

529.061 

1,049,282 



The contracts that include vehicles S-I78 through S-192 are listed in table XXXV 
for each Phase VI Scout vehicle. The table includes statistics on payload 
launch year, and vehicle contract listings for the hardware procurement, each 
motor stage, processing, and launch services. Table XXXVI lists the system 
engineering and software contracts for each Phase VI vehicle. 

Scout contracts were not separated by phases. Even in the case of contract 
NASI-7199, many motors manufactured on this contract were assigned to Scout 
vehicles other than Phase VI, even though all the fifteen sets of vehicle 
hardware of this contract were Phase VI. Tables XXXVII through XL IX outline 
details of the following major contracts: 



NASI -5610 
NASI -6020 
NASI -71 02 
NASI-7199 
NASI -7256 
NASI -9258 
NASI -10000 
NAS1-11400 
NASI-I25OO 
NASI-I3IOO 
NASI -14200 
NASI -15000 
NASI -151 00 



Table 
Table 
Table 
Table 
Table 
Table 
Table 
Table 
Table 
Table 
Table 
Table 
Table 



XXXVI I 
XXXV I I I 
XXXIX 
XL 
XLI 
XLi i 
XLI II 
XLIV 
XLV 
XLVI 
XLV I I 
XLV I I I 
XLIX 



"Itemized in this chapter. 
-"Itemized in chapter 8. 



136 



ORIGINAL PAGE tS 
OF POOR QUALITY 



TABLE XXXV - SUMMARY OF PHASE VI VEHICLE CONTRACTS 



VEHICLE 



I78C 



179CRR 



180c 



181C 



182c 



183c 



184C 



185c 



t86C 



t87C 



I88C 



189c 



190c 



191c 



(1) 



PAY LOAD 



NAVY 



AIR FORCF 



192c 



OA-I 



PA- I 



NAVY 



PA- I 



OAST 



ESRO 



GERMANY 



PA- I 



UK 



PA- I 



PA- I 



PA 



NAVY 



LAUNCH 
YEAR 



_2i. 



7oR 



71 



72 



72 



71 



72 



72 



T* 



T* 



7h 



T* 



7h 



T* 



80 R 



VEHICLE-CONTRACTS 



PRODUCTION 



NASI -7 199 



NASI -7! 99 



NAS I -7199 



NASI -7 199 



NAS 1-7 199 



NAS 1-7 1 99 



NAS I -7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1 -7 1 99 



NAS 1-7 199 



NAS 1-7 199 



NAS I -7 1 99 



NASI-7I99 



CERTIFIED 



NASI -725b 
NASI -1 0000 



NAS1-i2!>00 

mvmo 



NAS 1-1 0000 



NAS 1-1 0000 



NAS 1-1 0000 



SERVICES 



NASI -10000 



NASI -12500 



NAS 1-1 0000 



NAS 1 - 1 0000 



NASI -10000 



NASI -10000 



NASI -10000 



NASI -10000 



NASI -10000 



NASI -10000 



NASI -12500 



NAS 1-1 0000 



NASI -10000 
NASI -12500 
NASl-iZiOU 
NASI -15000 



NASI -10000 



NAS 1-1 0000 



NAS 1-1 0000 



NASI -10000 



MOTOR CONTRACT - STAGES 



FIRST 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-9258 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-9258 



NASI -9258 



NAS 1-12500 



NAS 1-1 2500 



NASI -12500 



NASI -12500 



NASI -12500 



NASI -12500 



NASI -15000 



NASI -9258 



NAS 1-7 199 



NASI -9258 



NASI -9258 



SECOND 



NASI-7I99 



NAS 1-7 199 



NAS 1-7 1 99 



NAS 1-7 199 



NAS I -7 199 



NAS I -7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1 -7 1 99 



NASI -71 99 



NAS 1-7 199 



NAS 1-9258 



NASI -9258 



NASI -13100 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NASl-n'tOO 



THIRD 



NAS 1-7 199 IAS 1-5883-3 



NASl-llitOO 



HASl-ll'tOO 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 



FOURTH 



NASI-56IO 



NASI -71 99 



NAS 1-7 1 99 



NASI-56IO 



NASI-7I99 



NAS 1-56 10 



NAS 1-7 199 



NAS I -7 199 ^ASI-llttOO 



NAS 1-7 199 



NAS 1-7 199 



NAS 1-7 199 ;NASI-1I')00 



NASI -71 99 



NASl-ll'tOO^IASI-7199 



NASI -l'*200gASl- 1^*200 



NAS I -7 199 



(1) 



Fifth stage - NAS1-7102. 



TABLE XXXVI - SUMMARY OF SOFTWARE CONTRACTS FOR EACH PHASE VI SCOUT VEHICLE 



(1) 



Vehicle 


Pay load 


Launch 
Year 


Payload Coordination 


Pref light 
Planning 


Data 
Reduction 


Systems Engineering 




General ^^^ 


Prel ini.Traj 


■ Speiiai 
• Studies 


Production 


Certified 




I78C 


Navy- 16 


73 


10000- 12500 


- 




10000 


12500 


6020 


7256 




179CRR 


AIR FDRCt 


76 


10000-12500 


7256-12500 


12500 


10000-N 
12500-A 


1250 


6020 


7256-10000 
12500 




180C 


CAS-A(EOLE) 


71 


"6020-- 725s 
10000 


7256 


6020 


10000 


10000 


7256 


10000 




18ICR 


GRS-A2(AER0S 


) 72 


7256-10000 


7256 


10000 


10000 


10000 


7256 


10000 




I82C 


Navy- 15 


72 


- 6U2U- /256 
10000 


- 


- 


10000 


10000 


7256 


10000 




183C 


UK-it 


71 


7256-10000 


7256 


7256 


10000 


10000 


7256 


10000 




181C 


CAS -8 


Canceled 


10000 


- 


- 


- 


- 


7256 


•* 




. 


MSS-A(P&FA) 


Canceled 


7256 


7256 


7256 


- 


- 


- 


- 




l8itC 


MTS-A 


72 


10000 


10000 


10000 


10000 


10000 


7256 


10000 




185c 


ESRO- IV 


72 


7256-10000 


10000 


10000 - 725f 


10000 


10000 


7256 


10000 




186C 


AEROS-B 


7k 


10000-12500 


12500 


10000 


12500 


12500 


7256 


10000 




187c 


UK-5 


T* 


10000-12500 


10000 


10000 


12500 


12500 


7256 


loooo 




188 


UK-Xi* 


Ih 


1 0000- 12500 


10000 


10000 


12500 


12500 


7256 


10000 
1 




I89 


ANS-A 


Ih 


10000-12500 


10000 


loooo 


12500 


12500 


7256 


12500 




190 


SM-C2 


T* 


10000-12500 




7256 


12500 


12500 


7256 


loooo 




191 


NPE-A 


74 


10000-12500 


10000-12500 


10000 


12500 


12500 


7256 


10000-1250 


) 


192 


NAVY-20 


81 


15000 


- 


- 


15000 


15000 


7256 


12500-1 50c 






(^)aII contract numbers are preceded by "NASI-." 

(^^Includes General Coordination, interface drawings, and heat shield and umbilical designs. 



< MJ*^'!^^^ i$d^l»:;M^)M^m^mf^f-'i»^s^^^,^i»i^mXAM<^^mm&ms^imipm^^S^i 



BIACK And WHITE PHOTOGRAPH 





£ 



sr 



* 




o 
m 

c 
o 



:3 
O 
O 

CO 



o 



3 
o 



ro 
o 



o 

x: 

I 

so 



3 



Pl-A^ 



t3S 







,:-mi 



'*^'/ 



*3y t. \-v'^"„; \C ' --^^XA^i J^- ' 



.., j-p 

wllffliiiiiii ■■trMJmiiiiim 




CO 






O 

>■ 

ffi] 



(0 

c 
c 



c 

V 

+-> 

c 



:3 

-M 

w 
O 



TO 
O 



CL 



I — 



<U 






139 



TABLE XXXV ft 



SCOUT - NASI -5610 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



Contract 



TOTAL 



15 Scout Vehicles less Motors 



Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 
Scout 



163 

]ek 

165 
166 

167 
168 

169 
170 
171 
172 
173 
17^ 
175 
176 
177 



$6,901,500 



Transition C Structure 
Transition Lower D Structure 
Heat Shield 



17 Algol Rocket Motors (1 Q.A.) 



IIB-59 
IIB-60 
IIB-61 
IIB-62 
IIB-63 
IIB-64 
llB-65 
116-66 
IIB-67 
IIB-68 
IIB-69 
llB-70 
IIB-71 
IIB-72 
IIB-73 
IIB-7^ 
1 18-75 



Scout 

Scout 

Test 

Scout 

Scout 

Scout 

Scout 

Scout 

Scout 

Scout 

Scout 



161 
168 



18,350 

6,655 

16,500 

2,160,700 



160 
172 
167 
164 

175 

169 

174 

163 

Shelf Life Study 
Scout 166 

171 

165 

173 

176 



Scout 
Scout 
Scout 
Scout 

3 Algol Nozzle Assembl ies (Spare) 

4 Algol Igniter Assemblies (Spare) 
2 Algol Squib Retainers (Spare) 

2 Algol Nozzle Leak-Check Tooling 



52,140 

3,340 

352 

1,490 



140 



TABLE XXXVI I Continued - 



SCOUT - MAS 1-5610 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



TOTAL 



Contract 










15 Castor 1 1 


Rocket Motors 


$1,495,200 




170 Scout lb2 






171 Scout 169 






172 Scout 165 






173 Scout 167 






174 Scout 164 






175 Scout 174 






176 Scout 171 






177 Test 






178 Scout 163 






179 Scout 172 






180 Scout 175 






181 Scout 177 






182 Scout 173 






183 Scout 166 






184 Scout 176 






1 Castor Py 


rogen Igniter (Spare) 


1,693 




16 Antares X 


-259 Motors 


912,960 




B3-211 


Reject - Test, AEDC 






B3-212 


Scout 15a 






83-213 


Scout 162 






B3-214 


Scout 172 






B3-215 


Scout 165 






83-216 


Scout 167 






83-217 


Scout 169 






B3-218 


Scout 1 74 






83-219 


Scout 176 






83-220 


Scout 157 






83-221 


Scout 171 






83-222 


Test, AEDC 






83-223 


Scout 177 






83-224 


Scout 173 






B3-225 


Scout 144 






B3"22b 


Scout 175 






16 FW-4S Motors 


529,120 




2223-1 


Scout 167 






2223-2 


Scout 168 






2223-3 


Scout 1 74 






2223-4 


Scout 165 






2223-5 


Scout 169 






2223-b 


Scout 172 






2223-7 


Scout 177 






2223-8 


Scout 144 






2223-3 


Scout 171 






2223-10 


Scout 175 





-onoo« ^ 



Amendments 



M-1 
M-2 
M-3 



M-5 
M-6 
M-7 

M-8 



M-9 



M-10 

M-11 
M-1 2 

M-1 3 
M-14 
M-1 5 
M-16 



141 



TABLE XXXVII Concluded - SCOUT - NAS1-5610 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

TOTAL 
Contract, Continued 

16 FW-4S Motors - Continued 

2223-11 Scout 166 

2223-12 Scout 183 

2223-13 Scout I85 

2223-14 Scout 173 

2223-15 Scout 180 

2223-16 Scout 163 











$12 


,100,000 


(Funding Decrease) 


-$1 


.000,000 






(Fund ing) 




$3 


,100,000 


$3 


,100,000 






$ 


34,695 


$ 


34,695 


(CCN's 1, 2, 5) 
CCN-1 
CCN-2 
CCN-5 




$ 


-5,100 
6,500 
2.114 


$ 


3,514 


Admin. Change 




$ 





$ 





(CCN's 6, 8, 9) 1 


Deletion 


Initiators $ 





$ 





(CCN's 3, 10) 
CCN-3 
CCN-1 




$ 


23,696 
52.740 


$ 


76,436 


(CCN's 7. 12, 13) 
CCN-7 
CCN-12 
CCN-13 




$ 


9,500 

2,400 

11.950 


$ 


23,850 


(CCN's k, 14, 15) 
CCN-4 
CCN-14 
CCN-15 




$ 


1,000 
5,600 
2.300 


$ 


8,900 


(CCN's 16, 17) 
CCN-16 
CCN-1 7 




$ 


10,500 
56.630 


$ 


67.130 


(See M-1 5) 




$ 





$ 





(See M-1 5) 




$ 





$ 









$ 


3,205 


5 


3,205 


Del ivery Schedule 


Change 


$ 





$ 





(M's 11, 12) 




$ 


1,257 


$ 


1.257 






$ 


24,846 


$ 


24,846 






TOTAL CONTRACT 
TOTAi niunpn 


$12,343,833 




t19 


«ii9 Rl3 



142 



TABLE XXXVIII - SCOUT - NASl-6020 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

A. Administration 

B. Payload-02 

C. Pref light Planning-02 

D. Data Analysis-02 

E. Systems Engineer ing-02 

F. Rel iabil ity-02 

G. Standardization-02 

H. Support to Veh. Checkout (Phase IV)-01 

J. Vehicle Modifications & Checkout-OI 

K. Vehicle Checkout (Phase V)-01 

L. Logistics-01 

M. Wallops Island Field Team-02 

N. AFWTR Field Team-02 

P. Langley Research Center Field Team-02 

R. Vehicle Failure I nvestigat ion-03 

S. Emergency Propulsion Sys. Support-01 o 

T. Customer Responsibility Changes 

TOTAL FUNDED ($6,737,100) 

Mod. 1 (incentive Change) 

Cork-Base A - Task J 

Deutsch Connectors - Task J 

Switching Relay Mod Kit - Task J 

Delete Magnetic Pick-ups - Task J 

Training - Task N 

Delete AFWTR Field Team - Task N 

Mod. 2 (Funding $511,604-) 

Mod. 3 Funding ($1,90^.628) 

Rework EGSE and MGSE - Task H 
Mod. k 

Return Crew to Dallas - Task M 
Mod. 5 Funding ($511,604) 

Mods, to Standard Procedures - Task G 
Mods, to EGSE - Task H 
Mod. 6 

X-258 Off-site Rep. - Task E 
X-258 RMRB - Task E 
Update Spares Inventory - Task L 
Mod. 7 



TARGET 


TARGET 


TARGET 


COST 


PROFIT 


PRICE 


$1,885,272 


$185,699 


$2,070,971 


200,039 


19.704 


219,743 


268,077 


26,406 


294,483 


759.858 


74.846 


834,704 


1,861,123 


183,314 


2,044,437 


1,235.272 


121.675 


1,356,947 


797,591 


78.564 


876,155 


394,574 


38,866 


433,440 


732,964 


72,197 


805,161 


1.151,123 


113.387 


1,264,510 


459.907 


45.301 


505,208 


1.697.137 


167.169 


1,864,306 


486,078 


47,879 


533,957 


336,985 


33,193 


370.178 











r-02 

















$12,266,000 


$1,208,200 


$13,474,200 











3.969 


390 




4,075 


401 




5,723 


564 




(3,482) 


(342) 




5,679 


560 




(481.694) 


(47,447) 




$(465,730) 


$(45.<i7M 


$(511,604) 












7.890 



79.086 

10,134 

18.249 

$28,383 

74,681 

9,265 

20.125 

$104,071 



777 



998 

1.797 
$2,795 

8.145 

124 

1.982 

$10,251 



8,667 



79,086 



$31,178 



$114,322 



1/*3 



TABLE XXXVII I Continued 



SCOUT - NASI -6020 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



FIXED PRICE 



Call 
Call 
Call 
Call 
Call 
Call 
Call 
Call 
Mod. 



No. 


1 - 


Spares 


$ 7.213 


No. 


2 - 


Spares 


1,930 


No. 


3 - 


Spares 


6,086 


No. 


k - 


Spares 


24,768 


No. 


6 - 


Spares 


23,257 


No. 


7 - 


Spares 


35,970 


No. 


8 - 


Spares 


12,374 


No. 


10. 


Spares 


2,078 



8 - Spares 



TASK L 



Mod. 9 Funding ($4,320,868) 

Off-site Quality Rep., FW4S - Task E 
Heat Shield Mods, and Fit Checks - Task 
Applic. Cork, Base A Fins - Task K 
Mod. 10 



Call 
Call 
Call 
Call 
Call 
Call 
Mod. 

Penal 
Mod. 



No. 
No. 
No. 
No. 
No. 
No. 
11 ■ 



5 - Spares 
9 - Spares 
1 1 - Spares 

12- Spares 

13- Spares 

14- Spares 
■ Spares 



99,396 
29,136 

2,337 
18,648 
42,988 

5.814 
TASK L 



ty - Task E 
12 



(S-152 Failure) 



TARGET 
COST 





$ 26,218 

13,400 

5.745 

$ 45,363 



TARGET 
PROFIT 





$ 2,582 
1,319 

565 

$ 4,466 



Call No. 15 ■ 

Call No. 16 ■ 

Mod. Filters 

Mod. 13 



Failure Invest., S-152 - Task R $162,000 
X-259 Tests, S-152 - Task R 77,000 

24.400 
$263,400 



Task K 



i-375.000 
$-375,000 

$15,957 
7,585 
2.400 

$25,942 



Call 
Can 
Call 
Call 
Call 
Call 
Call 
Call 
Mod. 



No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
14 - 



17 

19 
24 

25 
26 
27 
29 
33 



Spares 
Spares 
Spares 
Spares 
Spares 
Spares 
Spares 
Spares 



Spares 



785 

9.717 
11,918 

1,450 
165 

1,287 

3,505 
_ 734 
TASK L 



TARGET 
PRICE 



$113,676 




$ 49,829 



$198,319 
$ -375,000 

$289,342 



$ 29,561 



144 



TABLE XXXVI I I Continued 



SCOUT - NASI -6020 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



FIXED PRICE 

CCN No. 5 - Change in P/L Assignments - Task J 
Call No. 22 - Tests Base A Sect., S-I58C - Task R 
Call No. 32 - Replacement, Veh. Components - Task 
Return Crew to Dallas - Task M 
Off-site Qual. Rep., X-258 - Task E 
Audit Subcontractor - Task F 
Adding NASl-7199 Tool Maintenance - Task H 
Mod. 15 



Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Mod 



No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
16 



CCN-4 
Call No. 
Mod. 17 

CCN-6 
Mod. 18 



18 
20 
21 
23 
30 
31 
34 
35 
38 
39 



28 



Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Cal 
Mod 



No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
19 



36 

37 
41 

45 
47 
48 

49 
54 
56 
57 



Inspect 5 X-259 Motors - Task S 
Decontaminate Algol IIB-I7 - Task S 
X-258-130 Stat. Fire (Prep.) Task S 
Igni ters - Task S 

Change Nozzle on Algol 118-20 - Task 
Replace Algol I I B-53 on S-157 - Task 
Rework Algol IIB-55 - Task S 
Modify 16 X-259 Nozzles - Task S 
Explosive Bolt Shelf Life - Task S 
Repair Castor Drill Jig - Task S 



Rev. Scout Stand. Procedures 
Test Base A, S-I57C - Task R 



Task G 



Base A Fairings, S-160-162 - Task J 



Prep, for Ship., X-259 Motor - Task S 
Aging Prgm. for X-258 Mtrs./lgn. -Task S 
Fourth-Stage Initiators - Task S 
Batch Test Motors - Task S 
Instru., FW-4S Rocket Mtr. - Task S 
Shelf Life Ext. M-125 Init. - Task S 
Rework Algol IIB-55 '9"- Sleeve - Task S 
Removal X-258 Nozzle - Task S 
Fab. Aft Insul. Mold, X-259 Mtrs.- Task 
X-ray Castor Rocket Mtr. Noz. - Task S 



TARGET 




TARGET 


TARGET 


COST 




PROFIT 


PRICE 


$ 7.000 


$ 


690 




1,210 




119 




48,700 




4.797 




10,998 









11.835 




1,166 




4,898 




482 




48 , 249 




^,753 




$132,890 


T 


12,007 


$144,897 


$ 18,882 


$ 


1,416 




534 




40 




17.573 




1.338 




9.328 




681 




881 




68 




2,970 




190 




1.988 




155 




5,808 




407 




297 




21 




1.368 




109 




$ 59.629 


T" 


4.425 


$ 64,054 


$ 10,500 


$ 


1,034 




3.899 




384 




$ 14,399 


T 


1,418 


$ 15,817 


^ 1,275 


? 


120 




$ 1.275 


$ 


120 


$ 1,395 


$ 612 


$ 


45 




74,861 




5,907 




3.866 




257 




3.241 




219 




11,656 




1,146 




684 




52 




2,081 




166 




2,061 




141 




10,558 




752 




27? 




63 





$110,599 $ 8,748 $119,347 



145 









TABLE XXXVIII Continued 










FIXED PRICE 


Call 


No. 


40 - 


Spares 


$ 2,125 


Call 


No. 


42 - 


Spares 


65,025 


Call 


No. 


43 - 


Spares 


6,771 


Call 


No. 


44 - 


Spares 


5,812 


Call 


No. 


46 - 


Spares 


1,767 


Call 


No. 


50 - 


Spares 


4,900 


Call 


No. 


52 - 


Spares 


1,606 


Call 


No. 


53 - 


Spares 


15,987 


Call 


No. 


55 - 


Spares 


4,549 


Call 


No. 


58 - 


Spares 


1.157 


Call 


No. 


59 - 


Spares 


2.305 


Mod. 


20 


-Spa 


res 


TASK L 


Mod. 


21 


(See 


•iod. 29) 


- Task K 



SCOUT - NASI -6020 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



TARGET 
COST 



TARGET 
PROFIT 



TARGET 
PRICE 



Mod. 22 (See Mod. 25) - Task K 

Mod. 23 (See Mod. 29) - Task K 

CCN-7 - instrumentation for S-161 
Mod. 24 

Mod. 25 (Cancel Mod. 22) - Task K 

Mod. 26 (See Mod. 37) - Task B 



- Task K 



Penalty 
Mod. 27 



Task E (S-160 Failure) 









$ 


112,004 


$ 


$ 





$ 





$ 


$ 





$ 





$ 


$ 





$ 





$17,200 


$ 1 


,700 


$ 


18,900 


$ 


$ 





$ 





$ 


$ 





$ 





? < 


> -375 


,000 







$ -375,000 



Call 
Call 
Call 
Call 
Call 
Call 
Call 
Call 
Mod. 



No. 
No. 
No. 
No. 
No. 
No. 
No. 
No. 
28 



60 - Spares 

62 - Spares 

63 - Spares 

64 - Spares 

65 «' Spares 

66 - Spares 

67 - Spares 
70 - Spares 

■ Spares 



13,675 
5,302 
3,025 
4,470 
3,820 
8,375 
165 
1.749 

TASK L 



$ 40,581 



M-21 - Red. 
M-23 - Ext. 
Mod. 29 



1st £• 2nd Stg. Hdcp. Pres.Tub. - Task K 
Shelf Life EX-38 Pres.Cart. - Task K 



$ 8,375 

i.715 

$10,090 



$ 



835 
HI 



$1,010 $ 11,100 



\k6 



TABLE XXXVIII Continued - SCOUT - NAS 1-6020 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



Call No. 
Mod. 30 

Mod 31 - 

Mod. 32 

Mod. 33 

Mod. 3^ 



Call No. 
Call No. 
Can No. 
Call No. 
Mod. 35 

Mod. 20 
Mod. 28 
Call No. 
Call No. 
Call. No. 
Call No. 
Call No. 
Call No. 
Mod. 36 

Mod. 22 
Mod. 26 
Mod. 37 

Mod, 37 

Mod. 38 



FIXED PRICE 
51 - S-160C Flight Anomaly Invest. -Task R 

Off-site Quality Rep. at UTC - Task E 

- Cancel, of Prep, for Ship.X-259 Chamb.-Task S 

- Termination of 5 Vehicles-Tasks B, C, D, E, $ 

F, G, H. J, K, T 

- Termination of 5 Vehicles-Tasks B, C, D, E, 

F, G, H, J 

61 - Radiography, Algol Nozzle - Task S 

63 - Prep, of X-258 Motor for Shipment- Task S 

73 - FW-i4S Nozzle 30302 Leak Test - Task S 

77 - Inspect. Castor MA Nozzle Tool - Task S 



(Revised) Spares $ -630 

(Revised) Spares -888 

65A - Spares 1,333 

68 - Spares 22,^k8 

72 - Spares 13.510 

7k - Spares 21,80U 

75 - Spares 459 

76 - Spares 4.965 

TASK L 

- Dyn. Bal. Upper D Section - Task K 

- P/L-to-Veh. Compatibility Analysis - Task B 

- Canceling Mod. 22, Redes. 1st and 2nd Stg. 

Headcap Pressure Tubing - Tasks B. K 



Retransfer Expenses of Personnel from 
Wallops Station - Task M 



TARGET 
COST 


TARGET 
PROFIT 




TARGET 
PRICE 


$67^,000 


$40,000 


$ 


714,000 


$ 6,752 


$ 668 


$ 


7,^20 


$ -612 


$ -k5 




-657 


-769.095 


$-60,000 


$ 


-829,095 


$ 


$ 


$ 





$ 2,330 

3.137 

325 

36A 


$ 160 

220 

21 

27 







$6,156 $ 428 $ 



6,584 









$ 


63,001 


$ 1.500 

A.700 

-1.530 


$ 




450 




$ 




$ i»,670 


$ 


450 


5,120 


$-27,037 


$ 





$ 


-27.037 



Mod. 39 - Incentive Fee, S-I6OC - Task E 



$250,000 $ 250,000 



147 



TABLE XXXVI (I Concluded - SCOUT - NASl-6020 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



FIXED PRI CE 

Mod. ^40 - Change in Contractor's Division Name 

Mod. k] - Underrun - Task E 
Asset Set Aside 
Employee Benefit Plan 
Workmanship Incentive 
Underrun 



Mod. m - Termination Sale Mat'l Credit-Task E 



TARGET 
COST 



$ 23.881 

97,Oit5 

3.525 

-579.397 

? -1^42 



TARGET 
PROFIT 

$ 







$ 2.352 





$ 2,352 





TOTAL CONTRACT 



TARGET 
PRICE 



$ -i446.l43 
-1^2 

$13,'t89,722 



TABLE XXXIX - SCOUT - NAS 1-7102 (CONTRACT HISTORY) 

HERCULES INCORPORATED 

Amendment I tern 

Contract Casting Powder (GFE) 

1 BE3A9 Mockup $1 1 ,300 

1 BE3A9 Inert Motor 37,000 

2 BE3 AEDC Test Motors 74,000 
1 Balance Fixture 5,000 
16 Spare Detonators 3,200 
Documentation 18,500 
6 BE3A9 Motors 222,000 

AN09/001 Inert 

AN09/003 Scout 191 

AN09/005 Test/Shelf Life 

AN09/006 

AN09/008 

AN 09/010 Used by Germany on Firewheel Program 

M-1 (CCN !, 2, 3) Design Improvements & Additional Tests 

W-2 Change fn Government Furnished Property Clause 

M-3 BE-3-A1 Ignitor Mods. (CCN-l) 

M-4 Schedule Change 

M-5 Mods, to Test Fixtures. BE-3A-9 Test Program 



Cost 
$371,000 



$101 ,875 
$ 
$ 54,200 
$ 
$ 1^450 



TOTAL CONTRACT 



$528,525 



Contract 



Amendments 



M-1 (CCN-1) 



}k8 



TABLE XL - SCOUT - NASl-7199 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



""IS Scout B Vehicles(S-178-S-192)($6,639,5i»0) 

(Funding $4,500,000) 
2 Heatshlelds ($i»4,556) A-73, A-74 
2 Castor Igniters {$6,k\k) 
17 Castor II Motors (less ini tiators) ($1 ,635,655) 

185 Scout \kk 

186 Scout 180 

187 Scout ]8k 

188 Scout 185 

189 Scout 187 

190 Scout 190 

191 Scout 181 

192 Scout 183 

193 Scout 179 
19A Scout 178 

195 Scout 170 

196 Scout 197 

197 Scout 182 

198 Scout 188 

199 Scout 191 

200 Scout 186 

201 Scout 189 



16 X-259 Motors (Funding $it00,O00) 



TOTAL 



$8,326,165 



$1,187,002 



301 


Scout 


166 


302 


Scout 


183 


303 


Scout 


184 


30k 


Scout 


170 


305 


Scout 


163 


306 


Scout 


190 


307 


Scout 


187 


308 


Scout 


188 


309 


Scout 


195 


310 


Scout 


178 


311 


Scout 


182 


312 


Scout 


185 


313 


Scout 


181 


314 


Scout 


180 


315 


Scout 


186 


316 


Scout 


189 



"Includes heat shields A-58 through A-72. 



149 



TABLE XL Continued - SCOUT - NASI -71 99 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

Amendments Continued TOTAL 

M-2 (Funding $1 ,900,000) 

M"3 Schedule Change $q 

M-^ 2 Algol igniters (Less Initiators) $8,720 

1 Nozzle Housing 2 833 

17 Algol lie Motors (Funding $700,000) 2,086,'2'»0 

76 Scout 177 

77 Scout ]kk 

78 Scout 180 

79 Scout 187 

80 Test 

81 Unassigned 

82 Unassigned 

83 Scout 179 
8k Scout 182 

85 Reject - Replaced by 93 

86 Scout 178 

87 Unass igned 

88 Unass igned 

89 Scout 183 

90 Unassigned 

91 Unassigned 

92 Unassigned 

93 Unassigned 

M-5 Modification of 500-lb Reaction Control Motor/Valve Assy. $6,690 

M-6 (See M-15) $0 

M-7 Transfer of GFE Tooling $0 

M-8 (Funding $3,000,000) 

M-9 Radiographic Inspection of Castor II Nozzle Inserts $7,025 

M-10 (See M-ll) $0 

M-ll Procurement of Additional Components (See M-lA, No. lA) $0 

M-12 Procurement of the following: $35,6'«9 

Installation of Corl< to Base A Fins $11,200 

Winterization Kits 1,675 

QCEPS-012 Revision 21,350 

X-259 Field Assembly Improvement 1,42^ 



150 

TABLE XL Continued - SCOUT - NASl-7199 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

Amendments Continued TOTAL 

M-13 (Funding $500,000) $0 

M-1^ (Funding $1,485,324) $825,000 

Procurement of the following: 

B Section T/M Junction Box Assys. $ 32,000 

C Section T/M Junction Box Assys. 41,200 

Roll and Yaw Compensators 53,440 

Ground Cooling install. Compons. 2,325 

Lower D Sect. Elec. Bundle Assy. 110,400 

S-Band Antenna Sep. Compons. 17,152 

S-Band Telemetry Transmitters 136,880 

S-Band Telemetry Packages 369,435 

Battery Adapter Plates 47,330 

Coax Power Divider Brackets 1,428 

Dummy Roll and Yaw Compensators 1,080 

Vertical Shelf Gussets 4,950 

Tunnel Harness Disconnect Bracketry 855 

Lower D Sec. Elec. Harness Hardware 1,845 

Special Bushings 4,680 
(Includes Mods, to D Section Wiring Harness $8,700) 

M-15 (M-6) Mods, for Compatibil ity with SBASI $30,9^^8 

M-16 Procurement of 8 FW-4S Rocket Motors $603,496 



2376 - 


1 


Scout 


182 


2376 - 


2 


Scout 


181 


2376 - 


3 


Scout 


191 


2376 - 


4 


Scout 


190 


2376 - 


5 


Scout 


170 


2376 - 


6 


Scout 


186 


2376 - 


7 


Scout 


188 


2376 - 


8 


Scout 


184 



M-17 Winterization Kits $-1,936 

M-18 Repair 15 Algol II Handling Dollies $13,450 

M-19 Change in Government Furnished Equipment $-4,487 

M-20 Change in Delivery Schedule $0 

M-21 Change in Delivery Schedule $0 



151 



TABLE XL Concluded - SCOUT - NAS1-7199 (CONTACT HISTORY) 
LTV AEROSPACE CORPORATION 
Amendments Continued 



M-22 
M-23 
M-24 
M-25 
M-26 
M-27 
M-28 
M-29 



3 Tires for Algol MB Dolly 

Fabrication of Lower D Section Harnesses (SBASI) 

Vehicle Mods, to Accommodate Change froTi SBASI 

F\l-kS Leak Test 

Correction Minor Admin. Errors on Schedule 

Change in Contractor's Division Name 

Algol lie Storage at Aerojet General Corp. 

Change in Motor Delivery Schedule 

TOTAL CONTRACT 



TOTAL 

$277 

$1,620 

$11,056 

$5,000 

$0 

$0 

$24,000 

$0 



$13, 168, 7^*8 



TABLE XL I - SCOUT - NASI -7256 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



TASK 



A. 
B. 
C. 
D. 
E. 
F, 
G. 
H. 
A- J. 

K. 
L. 
M. 
N. 
P. 
R. 
S. 

-P 
I . 

V. 
W. 
X. 



Program Management 

Payload Coordination 

Preflight Planning 

Data Reduction and Analysis 

Systems Engineering 

Rel iabi 1 i ty Program 

Standardization & Configuration Control 

Support to Vehicle Processing 

Vehicle Processing (Phases I V.a. (S-l^tifRR) 

and V Vehicles) 
Vehicle Processing (Phase VI Vehicles) 
Logistics Support Management 
Logistics Support Materials 
Wallops Island Support 
Langley Support 
Failure Investigation 
Emergency Support 
Vehicle Processing Hardware 
Tooling and GSE Maintenance 
Certification Training 
Train i ng Film 



TOTAL FUNDED ($4,710,000) 





TARGET 




TARGET COST 


PROFIT 


TARGET PRICE 


$ 1,844,113 


$126,909 


$ 1,971,022 


157,601 


10,846 


168,447 


188,044 


12,941 


200,985 


485,933 


33,441 


519,374 


1,389,088 


95,594 


1,484,682 


1,273,269 


87,624 


1,360,893 


1 823,039 


56,640 


879,679 


202,637 


13,945 


216,582 


^R) 1,136, 035 


78,180 


1,214,215 


398,000 


27,390 


425,390 


429,547 


29,561 


459,108 


500,000 





500,000 


1,046,917 


72,047 


1,118,964 


288 , 298 


19,840 


308,138 




















363,3.30 


25,004 


388,334 


454,545 


3 1 , 280 


485,825 


31,968 


2,200 


34,168 


22,636 


1,??8 


24,194 


$11,035,000* 


$725,000 


$11,760,000 



--'-Includes ijOOK cost rei muursabl c Task M. 

#?r^oces''sed'"i66Pl, 170P2, 171P3, 172, 173, 174. 175, 176, 177, 
178, 163, I79P3, 144P2, 180P1 



152 



TABLE XL I Continued - SCOUT - NASI -7256 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

TARGET 
TASK TARGET COST PROFIT TARGET PRICE 

Mod. 1 S-166 D Section - Task J $ 7.950 $ 750 $ 8,700 

Mod. 2 Instrumented E-Section (See $ $ $ 
Mod. 6) - Task J 

Mod. 3 Install Cork to Base A Fins -Task K $ 2,750 $ 260 $ 3,010 

Call No. 1 - Shipping Material, S-163 $ 532 

Call No. 2 - Dwgs. and Specs. Emerg. Sup. 5,600 

Call No. 3 - Initiators and E-Sections 76,512 

Call No. 4 - San Marco Protective Barriers 4.797 

Mod. k (Funded) Task S** $ 87.441 

Mod. 5 Funding ($3,190,000) 

Mod. 6 Instrumented E Section (Mod. 2) - $ 68,000 $ 6,600 $ 74,600 
Task J 

Mod. 7 Roll and Yaw Compensation S-176 - $44,000 $4,280 $ 48,280 
Task J 

Mod. 8 Incorp. Instrumentation for SBASI $17,396 $1,675 $ 19,071 
Flight Evaluation - Task J 

Mod. 9 Ignition Mods - Tasks J, K $14,700 $1,400 $ 16,100 

Mod. 10 D Section Mods - Task K $28,900 $2,800 $ 31,700 

Mod. 11 Spec. Change, S-144 - Task J $ $ $ 

Mod. 12 Heat Shield Mods - Task T $ 6,975 $ 675 $ 7,650 

Mod. 13 Statement of Work Change - Task J $ $ $ 

Call No. 5 - Retest S-169 Guidance Sys. $ 8,858 

Call No. 6 - Mod. S-166 D Sect, P.L.Chng. 7,819 

Call No. 7 - Qual .Scout 4th-Stg.Lmt. Res. Box 6,524 

Call No. 8 - Elect. Eval.Tst. Scout Ign.Sep.Cir. 7,178 

Call No. 9 - Inspect. Castor II Rkt.Mtr.^WTR 2,396 

Call No. 10 - Inspect. Castor II at Wl 2,024 

Mod. 14 (Funded) Task S"" $ 34,799 



"•'"''•'Fixed Price. 



153 

TABLE XLI Continued - SCOUT - NAS1-7256 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

TARGET 
TASK TARGET COST PROFIT TARGET PRICE 

Mod. 15 Spec.Chg.to I nc.Proc.S-l63CR - Task KG $ $ 

Mod. 16 Retrans.Exp.for Wl Pers. 

from NAS1-6020 to NASl-7256 - Task N $27,037(Funded)$ $ 27,037 

Mod. 17 duality Rep. at UTC - Task F $19,033 $ 1,665 $ 20,698 

Mod. 18 Funding ($4,089,809) 

Mod. 19 E-Sect. Instrumentation (M-1 1 ,M-13)- $^9,850 $4,800 $ 5^.650 
Task J 

Call No. 12 - Fab. Scout Test Cables $ 4,08l 

Call No. 13 - Mods. S-166 and S-177 for 1,519 

GRP-A P/L Anten. Mount 

Call No. 15 - 10 Scout Base A Jet Vanes 19,600 

Call No. 17 - Inspect. Castor II Rckt. Mtr. 1,91^ 

Call No. 18 - Rework Scout Heat Shields 2,195 

Call No. 19 - X-258, X-259 Ign. Shelf-Life Vr. 10,195 

Mod. 20 Task S-'-v $ 39,504 

Mod, 21 VAFB Launch Services 7-1-70 to $1^10,070 $11,556 $ 151,626 
11-1-70 - Task N 

Mod. 22 Tooling and GSE Maint. - Task V $ 4l,692''~'- $ itl,692 

Call No. 8 - Eval. Tests Scout Ign. System $ -2,268 
Circuits 

Mod. 23 Task S $ -2,268 

Mod. 2k - Rev. Vol. Ill-Rocket Motor Manual $ QVrA- $ 

(SOP) (See Mod. 30^ - Task G 

Mod. 25 - Extension of Completion Date- $ $ $ 
Tasks C, D, F, G, K, M, T 

Mod. 26 - Tooling and GSE Maint. - Task V $ 1,778 $ 1,778 

Call No. 11 - Interim Pyrotechnics and $ 45,216 
GSE Requirements 



"'Fixed Price. 



15^ 



TABLE XLI Continued - SCOUT - NASI -7256 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

Call No. 16 - 

Call No. 21 - 

Call No. 23 - 

Call No. 2k - 

Call No. 25 - 

Call No. 26 - 

Cal 1 No. 27 - 

Call No. 28 - 

Call No. 29 - 

Call No. 30 - 

Call No. 32 - 

Mod. 27 



TARGET COST 

Flight Instrumentation 33,500 

Services for BE3-A9 Motor 2,834 

Assign/Reassign X-259 Nozzles 203 

Heat Shield Neg. Press .Tests 12,534 

X-258 Igniter Shelf-Life Prog. 39,838 

Inspection S/N-55 Algol MB Mot. 17,148 

T/M Signal Conditioning Unit, 26,627 

Roll & Yaw Comp. System (9) 

Extension Castor II Shelf-Life 75,065 

Program 

Inspect. Castor I lA Motor, 2,427 

S/N-184, at VAFB 

Algol III Test Components 1 ,607 

Crating Castor II Noz., 620-01 7 480 



TARGET 
PROFIT 



TARGET PRICE 



Mod. 28 - Mods, to Ignition Systems on 

Vehs. S-144, S-177, S-I63, and 
S-175, and Incorp. GFE on Vehs. 
S-178 through S-I8I - Task J 

Mod. 29 - Tech. at VAFB Sept. and Oct. 
1970 - Task N 

Mod. 30 - Reconstructure SOP, Vol. Ill 
(Mod. 24) - Task G 



Task S' 



$ 2,700 



$ 4.558 



$ 24,896 



Mod. 31 - Contractor's Division Name Change 
Mod. 32 - Change in Sched. of Mo. Bill. Prices 

Call No. 14 - Inspection T/M Package and $ 2,172 

Transmi tter 
Call No. 20 - X-258 Igniter Shelf Life $ 10,312 

Verification Program 
Call No. 22 - Algol I IB Motor Closure Assy, $ 6,307 
Call No. 31 - Proc. 13 E-Sections $ 93,340 

Call No. 33 - Fab. SOLRAD-C P/L Protective $ 2,448 

Shield 
Call No. 34 - Prep. Transition Section D $ 2,684 

for 42-inch Static Load Test 
Call No. 35 - Inspection Castor MA Motor $ 396 

Nozzle Tool 
Call No. 36 - Long Lead Time Components, $ 6,388 

S-144 



$135 



$450 



$2,427 



$ 257,479 
$ 2,835 



$ 


5,008 


$ 


27,323 













** Fixed Price, 



155 



TABLE XLI Concluded - SCOUT - NASI-7256 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

Call No. 37 - S-l^'t Special Instrumentation $ 17,55^ 
Call No. 38 - Reproduction of Documents $ 408 



TARGET PRICE 



Mod. 20 Credit - Two X-258 Igniters 

Mod. 33 

Mod. 3k - Incentive Award 

Mod. 35 - Credit - Decrease in Scope 

Mod. 36 - Extension of Completion Date 
Mod. X - Funded Retransfer of Personnel 



$ -1 .^00 
Task S** 



$ litO,609 

$ 425,000 

$ -589,669 

$ 

$ 27,037 



Mod. 37 



Final Price Redetermination 

Task M - Spares Actual $487,953 $-12,047 

- Retransfer of Personnel $8,ll0 $-18,927 

Task S - Emergency Support $557,564 

Target Cost Adjustment $10,591,277 Overrun $161,374 

Target Profit Adjustment 25% ($176,210) $-44,053 

Task V - Tooling & GSE Maintenance (F.P.) $43,470 



i. 



86 347 



TOTAL CONTRACT $ 1 2 , 781 , 00 



TABLE XLI I - SCOUT/NASI-9258 (Contract History) 



LTV AEROSPACE CORPORATION 



Contract Funded ($1,300,000) 

Design and Develop Algol III 
Production Tooling 

Engineering 11 ,642 liours 

Manufacturing 8,111 hours 

Materi al s 

U.T.C. Subcontract 

Development - 2,300,000 
Tooling - 170,000 

Di rect Charges 

G & A 

Profit 



$183,015 

86,582 

^6,235 

1,616,291 



98,263 
301,716 
137,898 



OPTION NO, 1 (10 Motors) $1,300,550 (Not Accepted) 
OPTION NO. 2 (i5 Motors) $1,301,880 (Accepted) 
OPTION NO. 3 (26 Motors) $3,225,300 (Not Accepted) 



AMOUNT 

$2,300,000 
170,000 



■'"''Fixed Price, 



156 

TABLE XLII - SCOUT/ NASI -9258 (Contract History) Concluded 
LTV AEROSPACE CORPORATION 



Mod. 1 Administrative Change $ 

Mod. 2 Funded ($668,000) 
SOP Mods 

Mod. 3 Case Test 

Mod. k Funded ($570,853) 

Mod. 5 Subcontractor Change 

Mod. 6 Change in Option Item, Statement of Work 

Mod. 7 Funded (OPTION NO. 2) 







lll-l 


S-170 


III-2 


S-184 


m-3 


S-181 


111-4 


S-185 


II 1-5 


Test 


II 1-6 


S-190 


II 1-7 


S-188 


111-8 


S-191 


111-9 


S-186 


111-10 


S-189 


111-11 


S-19^ 


111-12 


S-195 


111-13 


S-196 


111-1^4 


Reject 


111-15 


S-193 


111-16 


S-197 



$ 


61 


,200 


$ 


7 


.653 


$ 







$ 







$ 







$1 


,901 


,880 



Mod. 8 Contract Name Change 

Mod. 9 Specification Change Scout Tooling 

Mod. 10 SIJS - Waiver 

Mod. 11 Reduction in Unit Price for 2 Algol III Motors due 
to Extension of Period of Performance 

Mod. 12 Use of 2 GFE Algol III Motor Cases 

TOTAL CONTRACT 



$ 









-2 


500 




-2 


.^95 
-370 




-8 


,800 


$^ 


i»26 


,568 



157 



TABLE XLIII - SCOUT - NASl-10000 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

A. Program Management 

B. Payload Coordination 

C. Pref 1 ight Planning 

D. Data Reduction and Analysis 

E. Systems Engineering 

F. Reliability Program 

G. Standardization and Config. Control 
H. Vehicle Process 

J. San Marco Support 

K. Certification Training 

L. Logistics Support Management 

M. Spares 

N. Field Services Support 

P. Langley Program 

R. Special Programs 

S. Program Support 

T. Hardware 

V. Tooling and GSE Maintenance 

W. Failure Investigation 

TOTAL FUNDED ($6,437,000) 
Retransfer of Personnel (N) 



TARGET COST 


TARGET 
PROFIT 


TARGET PRICE 


$. 3,847,000 


,$275,000 


$ 4,122,000 


300,520 


21,480 


322,000 


382,650 


27', 350 


410,000 


878,220 


62,780 


941 ,000 


3,018,250 


215,750 


3,234,000 


1,713,520 


122,480 


1,836,000 


1,150.7A0 


82,260 


1,233,000 


1,517,530 


108,470 


1,626,000 


700,000 


49,000 


749,000 


39,200 


2,800 


42,000 


969,690 


69,310 


1,039,000 


500,000 





500,000 


4,376,180 


312,820 


4,689,000 


553,440 


39,560 


593,000 


600,000 


45,000 


645,000 



197,860 



14,140 



212,000 


711,200 


50,800 


762,000 











$21 ,456,000 
$ 158,976 


$1 ,499,000 
$ 


$22,955,000 
$ 158,976 



158 

TABLE XL I II Continued - SCOUT - NASI -10000 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

Mod. 1 Pricing Schedule Change 

Mod. 2 30 X-259 initiators-RAS159 (1 ,606) $ 

Task T (Funded) 



TARGET COST 




TARGET 
PROFIT 


TARGET PRICE 


$• 


$ 





$ 





$ 23,319 


$ 


1,527 


$ 


24,8it6 


$ 231, A54 
n Tips) 


$ 


20,831 


$ 


252,285 


$ 


$ 





$ 





$ 


$ 










$ 11A,016 


$ 


10,710 


$ 


12A,726 



Mod. 3 Jet Vanes and Fin Tips-RASl84,219 

Task T (Funded)(64-Jet Vanes) (32 Fin Tips) 

Mod. k Contractor Name Change 

Mod. 5 See Mod. 11 

Mod. 6 Algol III Fit. Hdwr. and GSE-RAS159 $ 
Task T 

Mod. 7 Funding ($200,000) -RASl 96 

Mod 8 Processing Vehs. l87 through 191 $ 
at Wallops Island - Task H 
(Canceled by Mod. 18) 

Call No. 001 - Inspection Castor MA $ 
Rocket Motor #'s 181,182,183 

Call No. 002 - Inspect., Pkg. and Crating 
S-173 

Call No. 003 - Rework and Test San Marco 
Separation Systems 

Call No. 00^4 - Provisions 32 RMS Finish on 
FW-4S Motor Components 

Call No. 006 - Furnishing Long Lead I terns 
for S-170 

Call No. 010 - Castor II Shelf Life Extens. 
Program and Aging Study 

Call No. Oil - Integration S/N 1 Fourth-Stg 

S-Band & S/N k2 E-Sectionon 180 

Call No. 012 - Purging and Vacuum Drying 
S-166 at Wal lops 

Call No. 014 - Modification A-63 Heat Shield_ 

Mod. 9 (Funded) -RASl 90 Task S"-- $ $83,671 

"Fixed Price -'-'-Later modified for UK-6. 



2 


,686 




989 


11 


,604 


2 


,740 


11 


,586 


47 


,050 


180 


.431 


3 


,053 




532 



159 



TABLE XLIII Continued - SCOUT 



NASI -10000 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



TASK 



Mod. 1 



Mod. II 



TARGET COST 



instal lation Algol III Hardware 
Thermal Protection - Task H 

(M5) Transportation to Support 
Launch Ops. at WTR-Task N 
(Funded $37,259) 



Mod. 12 Funding ($3,827,610) 

F.P.I. - (2,966,610) 
C.R. ( 861,999) 

Mod. 13 Task R Increase 
Task R Fee 
TOTAL MOD. 13 - Task R 

Call No. S-007 - GSE Mods, for SAS-B 
Call No. S-013 - fVI-l^S Motor Shelf Life 

Mod. ]k (Funded) 

Mod. 15 Fourth-Stage Ignition and 
Telemetry Sys.-Task T 

Call No. S-005 Furnishing Tool for 

Rocket Motor Igniters 
Call No. S-008 Algol III Thermal Insul. 
Call No. S-015 X-Ray X-259 Motor HIB-303 
Call No. S-016 Inspection Castor 11 Rkt. Mtr 
Call No. S-017 Inspection Equip. Use Training 



32,753 



$1,116,208 
83.716 



Mod. 16 (Funded) 



Mod. 17 Funding ($5,225,713) 



$ 19,500 
57,A28 

Task S* 

$ '♦13,132 

11,203 

18,223 
A, 028 
2,2i»0 
5,775 

Task S''= 



F.P.I 
C.R. 



(A,179,79A) 
(l,0if5,92A) 



Mod. 18 
Call No. 
Mod. 19 



Cancelation of Mod. 8 - Task H 
S-009 Recertif ication of S-170 
(Funded) 



$ 
135.850 
Task S-'^ 



TARGET 

PROFIT TARGET PRICE 



$ 



$ 2,300 $ 35,053 



$ 



$l,199.92it 



$ 76,928 
$ 36,150 $ /*i*9,282 



$ ^1.^69 



$ 



$ 



$ 135,850 



160 



TABLE XLIII Continued - SCOUT 



NASI -10000 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



TASK 
Mod. 20 

Mod. 21 

Mod. 22 

Mod. 23 

Mod. 2k 

Call No. 
Call No. 

Mod. 25 

Mod. 26 

Mod. 27 
Mod. 28 

Call No. 

Mod. 29 
Mod. 30 



Scout Hardware - Task T 
Scout Tooling - Task V 
(Funded) 

Fabrication A E Sections 
Task T 

Relocating Contractor Personnel 
(Definitized in Mod. 28) - Task P 

Spares - Task M (Funded) 

Funding ($2,600,000) 

, S-018 - Refurb. Scout B Section 
, S-019 - Battery Cells 

(Funded) 

Phase Vi I Production Support 
- Tasks E, F 



San Marco Support 
Task J 



(M22) Relocating Contractor 
Personnel - Task P 

W-001 - Single Point Failure 
Investigation - Task W 



(Funded) 

Funding ($5,852,193.00) 

F.P.I . - (5,000,000) 
C.R. - ( 852,193) 

Mod. 31 Scout Tooling - Task V 



TARGET COST 




TARGET 
PROFIT 


TARGET PRICE 


$ 2A,i.76 



$ 


2,325 



$ 


26,801 
6,A05 


$ 25,200 


$ 


2,300 


$ 


27,500 


$ 


$ 





$ 





$ 250,000 


$ 





$ 


250,000 



$ 9.315 
1,200 

Task S* 

$ 25^,365 

$ 235,827 
$ k,kk5 



$ 203,589 
$ 



$ 10,515 
$ 58.893 $ 313,258 

$ 16,508 $ 252,335 



400 



k,8k5 



$ 15,269 $ 218,858 
$ $ 



■6i.l 



$ 



-6itl 



"Fixed price. 



161 



TABLE XLIII Continued - SCOUT - NASl-10000 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

Call No. 020 Fab, Payload Protective Shield 
Call No. 021 Ultrasonic Standards for 

Algol III Motor 
Call No. 022 Retuning Command Dest. Receivers 
Call No. 023 X-258 Motor, S Igniter Shelf 

Life Extension Program 

Mod. 32 (Funded) 

Mod. 33 Task R increase 
Tasl< R Fee 

TOTAL MOD. 33 - Tasl< R 

Mod. 3^ Funding (2,027,802) 



TARGET COST 

$ 2,568 
6,3^1 

10,125 
^0,979 



Task S* 

$ 325.569 
2k, h3] 



TARGET 
PROFIT 



TARGET PRICE 



$ 60,013 

$ 350,000 
$ 



Mod. 35 San Marco Support-Task J 

Mod. 36 Task R Increase 
Task R Fee 

TOTAL MOD. 36-Task R 

Call No. 02^ Special Instrumentation Kits 

for X-259 Motors 
Call No. 025 Mods, to Vehicle to Accommodate 

New Safe Arm Units 
Call No. 026 Launcher Base A Support Pins 
Call No. 027 Repair Algol III Motor Raceway 

Drill Fixture 
Call No. 028 Assembly Fourth-Stage Ignition 
Call No. 029 Furnish Long Lead Items 

Mod. 37 (Funded) 

Mod. 38 Administration - Task R 



$ 228,970 $ 16,030 $ 245,000 



$ 460,473 
34,527 



$ 59,910 

43,116 

8,525 
7,469 

4,689 
4,955 

Task S'"^ 
$ 



$ 495,000 



$ 128,664 
$ 



162 



TABLE XLIII Concluded - SCOUT - 



NASI -10000 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



TASK 



Call 


No. 


S-O3O 


Call 


No. 


S-031 


Call 


No. 


S-O32 


Call 


No. 


S-033 


Call 


No. 


S-03^ 


Call 


No. 


S-O35 


Call 


No. 


S-036 


Call 


No. 


S-037 


Call 


No. 


S-O38 



GSE Changes 

Incorp.GFE Ignition Kits 

Acceptance Testing GFE 

BE-3-A9 Shlf. Life Ext. Prog. 

Algol II I Mod. Kits 

X-4 P/L Ignition Support 

Tone and Signal Generators 

4th Stg. Ign. and T/M Systems 

Thermistors 



Mod. 39 (Funded Task S) 

Mod. 40 Administrative Change 

Mod. k] Revision - Task R 

Mod. 42 Schedule Change - Task S 

Mod. 43 Extension Completion Date 

Mod. 44 Transfer of Funds from Task R to 
Task J ($75,000) 

Mod. 45 Substitution of Veh. 179 for 
Vehicle 190-Task S 



Mod. 46 Schedule Change 

Mod. 47 Under run 
Award Fee 

Mod. 48 Underrun - FPI 
Underrun - R 
(Retransfer Personnel 
(Decrease in Task R 

Mod. 49 Redetermined: 



$157,000) 
103,000) 





TARGET 








TARGET COST 


PROFIT 




TARGET PRICE 


$ 44,359 
8,162 










6,192 

47,900 

29,490 

981 

54,696 

1,301 
17,775 






$ 


210,856 


$ 


$ - 





$ 





$ 


$ 





$ 





$ -100 


$ 





$ 


-100 


$ 


$ 





$ 





$ 


$ 





$ 






$ 
$ 

$ -194,031 



$-1,110,000 

-260,000 



$ 



$ 



$ -13,995 $ -20R,026 
1,474,000 

$ 277.500 $ -832,500 

-260,000 



$ -143,788 



Summary: 



TOTAL CONTRACT 



TASKS A,B.C,D.E,F.G.H,K,L.N,P.T,Y (FPI) • 


■ $21,242,650 


W (Performance Award) 


1,474,000 


R (CPFF) 


2. 463, 109 (-48, 81 5) 


J (CPFF) 


1,300,387(-30,101) 


M (CPFF) 


721, 548 (-28, 452) 


Retransfer Field Personnel (FFP) 


1.976 


W (CPFF) 


209,705 


S (FFP) 


747,866 


V (FFP) 


5.764 



$28,167,005 



$28,167,005 



TABLE XLIV 



163 



SCOUT - NAS1-11400 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



Contract (Funding $2,819,000) 

.16 Castor I lA Motors ($1,565,952) 



TOTAL 
$3,819,000 







382 


S-195 






Case 


No. 


899 










383 


S-196 






Case 


No. 


900 










384 


Sandia S-202 




Case 


No. 


901 










385 


S-192 






Case 


No. 


902 










386 


Sandia Unassigi 


led 


Case 


No. 


903 










387 


Sandia S-203 




Case 


No. 


904 










390 


S-194 






Case 


No. 


905 










391 


Unass igned 






Case 


No. 


906 










392 


S-193 






Case 


No. 


907 










393 


S-200 






Case 


No. 


908 










394 


S-198 






Case 


No. 


909 










395 


S-201 






Case 


No. 


910 












1 


(Not 


Loaded) 


Case 


No. 


911 


(808 


Unass igned) 










(Not 


Loaded) 


Case 


No. 


913 


(809 


Unass igned) 










(Not 


Loaded) 


Case 


No. 


914 


(810 


Unass igned) 








1 


(Not 


Loaded) 


Case 


No. 


1399(811 


Unassigned) 




18 Antares 1 1 Mote 


)rs ($1,158,840) 














401 


S-191 






Case 


No. 


199 










402 


S-179 






Case 


No. 


200 










403 


AEDC Test 






Case 


No. 


205 










404 


S-197 






Case 


No. 


203 










405 


S-193 






Case 


No. 


206 










406 


S-196 






Case 


No. 


201 










407 


S-194 






Case 


No. 


202 










408 


S-200 






Case 


No. 


207 










409 


S-198 






Case 


No. 


209 






Case 


No. 


204 


Not Loaded 












Motor No. 410 Unassigned 


Case 


No. 


208 


Not Loaded 


(Mod 10) 








Motor No. 411 S-201 


Case 


No. 


211 


Not Loaded 


(Mod 10) 








Motor No. 412 S-202 


Case 


No. 


212 


Not Loaded 


(Mod 10) 








Motor No. 413 Unassigned 


Case 


No. 


2^k 


Not Loaded 


(Mod 10) 








Motor No. 414 Unassigned 


Case 


No. 


215 


Not Loaded 


(Mod 10) 








Motor No. 415 Unassigned 


Case 


No. 


216 


Not Loaded 


(Mod 10) Hydroburst 


(NASI 


-12500 R44) 


Case 


No. 


213 


Not Loaded 


(Mod 10) 












Case 


No. 


210 


Not Loaded 


(Mo< 


i 10) 













16 Antares II Nozzles ($2i6,480) (One nozzle to 211 Test) Less Initiator. 
6 Antares I IB Retainer Rings 



Goddard borrowed Case No. 912. All unloaded cases were GFP to contract NAS1-14200. 



TABLE XLIV Continued - SCOUT - NASI-llifOO (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

TOTAL 

1 Altair IMA Design Analysis and Demo Tests ($300,205) 

E01 Test-F (AEDC) 77° Alt. Test Case No. 007 

E02 Test-F (AEDC) 77° Alt. Test Case No. 005 

E03 Reject-Used for Analysis Deflection Case No. 001 

E04 Reject-And Sectioned Case No. 002 

E05 Reject-NDT-G.E. Case No. 004 

E06 Reject-NDT-G.E. Case No. 006 

E07 Test-F Demo-Sea Level kO° FA T.C. (PQ-1) Case No. 017 

E08 Test-Demo-Sea Level 77° F (PQ-2) Case No. 022 

E09 Qual. Test-Nozzle 013, Igniter 187-7 (SQ-I) 

i+0° sea level Case No. 018 

E10 Reject-Droopy liner Case No. 019 



19 Altair MIA Motors 


($572 


,166) 














Ell 


77" F 


Alt. 


test 


at T. 


C. 


Case No. 


021 










E12 


Test-RPL-Qual. 77° F 


Alt. Test at T.C. 


Ca 


56 No. 016 


E13 


S-187 


Case No. 


008 


NOZ2 


:le No. 006 




g 


liter No 


323-9 


E14 


S-189 






009 




016 










^?3-10 


E15 


S-195 






01i+ 




017 










323-12 


E16 


S-194 






020 




018 










323-13 


El 7 


S-197 






013 




019 










323-14 


E18 


S-196 






012 




020 










323-15 


E19 


S-193 






027 




021 










323-17 


E20 


S-200 






026 




022 










323-18 


E21 


S-179 






024 




023 










323-19 


E22 


NRL 






023 




010 










344-21 






UTC 


Test 


010 


(Case 


Only) (Mod 1 


4) 


E- 


-26 


(GFP 


to UTC.) 






UTC 


Test 


Oil 


(Case 


Only) (Mod 1 


^) 


E- 


-27 


(GFP 


to UTC.) 






H.E 


.P. 


015A(C3se 


Only) (Mod ^k) 


E- 


-25 


(H.E. 


p. Test, NAS1-12500) 






UTC 


Test 


025 


(Case 


Only) (Mod 1 


4) 


E 


-28 


(GFP 


to UTC.) 


E29 


s-198 






028 


(Case 


Only) (Mod 14) 










E30 


NRL 






029 


(Case 


Only) (Mod 1 


4) 










E31 


Unass i 


gned 




030 


(Case 


Only) (Mod 1 


4) 











1 Altair IMA Nozzle (004) ($5,357) - S-191 
Amendments 

M-1 New X-259 Retainer Rings $ 

M-2 Administrative Change $ 

M-3 Altair IMA Tooling $ 2,100 

M-4 Administrative Change $ 

M-5(M1) X-259 Hydrotests $ 7,858 

M-6 (Funding $1,009,958) 



165 



TABLE XL IV Continued - NASI -11^00 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

TOTAL 

M-7 Redirection X-259 Motors (103,791) $ 

M-8 Adminstrative Change $ o 

M-9 Delivery Schedule Change $ o 

M-10 Change in Motor Quantities Ordered (-^5^,353) $ 

Cancel Loading Castor II No. 2]k thru 217 
Cancel Loading Antares II No. AlO thru k]8 
Cancel Loading Altair MA Nos. 010, Oil, 015A, 
025, 028, 029, and 030 

M-11 Change in Acceptance Schedule 

M-12 Algol Nozzle Mods and Schedule Change 

M-13 Antares Nozzle Mods 

M-14 Decrease in Loading of 20 Motors (M7,M10,M1 1 ,M12,M1 3) 

4 Castors not Loaded (202,161) 

9 Antares II not Loaded (120,713) 

7 Altair III not Loaded (22,650) 

M-15 Finish 7 Altair III Nozzles 

M-16 dual. Firing One Altair I I I at Vendor's Facility 
(Incl. in M-17) 

M-17 Test Firing Altair III Motor E-12 

M-18 (M15) Finish 7 Altair III Nozzles 

M-19 Altair III Case Requirement 

Inspection Altair III Test Motor 

Extension of Delivery Date 

Antares MB Igniters (12) 

M-23 Addition of Igniter Hardware Components 
as Government Furnished Property 



(13,215) 


$ 





(-3,199) 


$ 





(-if, 968) 


$ 





13) 


$ 


-3^5,524 



M-20 


M- 


-21 


M- 


22 





$ 







$ 





(23,000) 


$ 







$ 


9,590 


(16,66A) 


$ 





(A, 600) 


$ 







$ 





(36,550) 


$ 





(17,103) 


$ 






166 



TABLE XLIV Concluded - NASI-H^OO (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TOTAL 



M-2A (M16,17,19,20) Altair III Motor $ kk ,Zek 

OUAL. Firing M16/17 
Spec. Change M19 
Inspect S/N Oil M20 

M-25 Change in Financial Reporting $ 

M-26 (M22,M23) Antares MB and Altair III Igniters $ 53,653 

M-27 Altair III Motor Case, Aft Plate, and End Fittings (8) $ 19,800 

(1) Altair III Rocket Motor Less Igniter ($13,853) 

(GFE Nozzle and Igniter) 

(2) 8 Aft Plate ($2,9^*4) 

(3) 8 End Fittings ($2, 280) 

M-28 Inspection Antares JIB Igniters $ 2,715 

M-29 Inspection Antares MB Igniters $ -1,596 

M-30 Name Change $ 

TOTAL CONTRACT $3,611,860 



^ 



167 



TABLE XLV - SCOUT - NASl-12500 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

A. Program Management 

B. Mission Integration 

C. Prefl ight Planning 

D. Data Reduction and Analysis 

E. Systems Engineering 

F. Rel iabi 1 ity Program 

G. Standardization and Configuration Control 
H. Vehicle Processing and Launching 

J. San Marco Support 

K. Certification Training 

L. Logistics Support Ma 



pport Management 



M. Logistics Support (Spares) 



N. Field Services Support (WFC/VAFS) 



P. Langley Progr 



ogram 



R. Special P 



rograms 



FUNDED TARGET COST 


TARGET 
PROFIT 


TARGET 
PRICE 


$ 3,161,861 


$ 221,108 


$ 3,382,969 


376,480 


26,328 


402,808 


158,216 


H,064 


169,280 


282,836 


19,779 


302,615 


1,979,540 


138,429 


2,117,969 


1.514,636 


105,918 


1.620,554 


788,284 


55,125 


843,409 


1,903,092 


133,083 


2,036,175 


279,432 


20,568 


300,000 


38,593 


2,700 


^1.293 


293,902 


20,553 


314,455 


465,721 


34,279 


500,000 


2,665,010 


186,363 


2,851,373 


437,760 


30.613 


468,373 


931.441 


68,559 


"1,000,000 



168 



TABLE XLV Continued 



TASK 



T. Vehicle Production Support 



SCOUT - NASI -12500 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 

TARGET TARGET 

FUNDED TARGET COST PROFIT PR ICE 

$ 213,599 $ 1^.937 $ 228,536 



V. GSE and Tooling Maintenance 

TOTAL 

MAXIMUM INCENTIVE AWARD 

TOTAL 



i+86,191 3^,000 520,191 



11 ^J'nnn'Snn $1 5, 976, 59^ ' $1 , 1 23.^06 $17,100,000 
CR 1 ,000,000 

800,000 800.000 

$l,923,'t06 $17,900,000 



M-1 Adjustment Man-hours and Material Charges 
Task J 

M-2 Administrative Change 

M-3 San Marco Support - Task J 



$ 



$ 



$ 



$ $ $ 

$ 227.907 $ 17.093 $ 2i+5,000 



H-k Funding - Tasks J, M 6- R 

CR. $745,000 

M-5 Adjustment Man-hours and Material Charges 
Task R 

M-6 Administrative Change - Task R 



$7^^5.000 $ 

$ 
$ 



$ 



$ 



$ 



$ 



$ 



$ 



M-7 Special Programs - Task R 



$ 930,194 $ 69,765 $ 999,959 



M-8 Schedule Revision 

M-9 Adjustment Man-hours and Material Charges 
Task M 



$ 
$ 



$ 
$ 








M-10 Logistics Support Materials - Task M 



$ 467.290 $ 32.710 $ 500,000 



169 



TABLE XLV Continued - SCOUT - NASI -12500 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



FUNDED 



TARGET COST 



TARGET 
PROFIT 



TARGET 
PRICE 



M-11 Incorporation Mod. Kits, Launch Facilities 
Task N 



M-12 Funding 



FPI 
CR 



M-I3 Addition of Two Vehicle Processings 
Tasi< H 

M-14 Increase in San Marco Support - 
Task J 

M-15 SPEAR Program 



$2,400,000 ^ 
1,2551000 $ 

$ 
S 

$ 



CCN S-001 Mod. S-I89 to Accept Algol III 

CCN S-002 Explosive Bolts 

CCN S-003 North Atlantic Phase Angle Voltmeters 

CCN S-004 Ablative Cork for Scout Vehicles 

CCN S-005 Fab. and Repl. Scout Tooling 



M-16 (Funded) 



Task S 



FPI 
CR 



M-17 Increase in Manhour Efforts 
Task R 

M-18 Funding 

M-19 (M-11 and M-I5) - Tasks H, N, P 
Performance Incentive 

M-20 Support to Algol III Procurement 
Under NASI -1 31 00 - Tasks E, F 



M-21 Increase in Manhour Effort - Task R 



$ 103,9^2 $ 
$ 

$4,250,000 <: 
1 1 000, 000 5 



$ 

$ 
707.39^ $ 



$ 




^9.716 



$ 
$ 757,110 



460,465 $ 34,535 $ 495,000 
$ $ 



11,855 
37,125 

8,900 

6,944 
39,118 

103,942 

929,246 $ 

$ 
^♦92,635 $ 



69,693 



43,106 
100,000 



$ 103,942 
$ 998,939 



$ 243,189 $ 22,617 
$ 2,093,023 $ 156,977 



535,741 
100,000 



$ 265,806 
$ 2,250,000 



M-22 Change in Financial Reporting 

M-23 Increase in San Marco Support - Task J 



$ 1,000,000 $ 



$ 
$ 1,000,000 



M-24 Funding 



FPI $1,750,000 t 
CR 2,500,000 5 



$ 



$ 



OF POOR OUAUTY 



170 



TABLE XLV Continued 



M-25 Spares - Task M 



SCOUT - NASI-I25OO (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



FUNDED 



TARGET COST 



TARGET 
PROFIT 



TARGET 
PRICE 



$ 916,659 $ 55,255 $ 971, 9H 



M-26 
M-27 

CCN 

CCN 
M-28 

M-29 

M-30 
M-31 
M-32 
M-33 

M-3A 

M-35 
M-36 

M-37 
M-38 



Schedule Change 
Performance Incentive 

6 "200" Series E Sections 

6 "25" Series E Sections 

S-006 

9 Algol III Mod Kits 

62 Jet Vane/Assemblies 

66 Fin Tips 

S-007 

(Funded) Task S 

Option - 2 Processings 
Tiask H 1% 

Increased Effort - Task R 

Administrative Change 

-Funding 

One Launch Option 
Performance Incentive 

Change from Mtls. to Labor in 
Task R 



FPI 
CR 



Failure Investigation 

Funding 

Performance Incentive Penalty 
for Vehicle 199 



CR 

FPI 
CR 



Decrease Task M 
increase Task R 

Decrease Task M 
Increase Task R 













s 







$ 


601,578 


$ 


i»2,273 
200,000 


$ 


6'»3,856 
200,000 




$ 
$ 


Si., '♦26 

8't,A26 

168,852 

486,8'»6 

395,560 

38,7'»2 












% 


921, U8 










$ 1,090,000 


$ 1 


,090,000 






$ 1 


,030,000 




$ 


707, 39'* 


$ 


49,716 


$ 


757,110 




$ 


930,233 


$ 


67, '.42 


$ 
$ 


997,675 



$ J, 250, 000 
1,800,000 


$ 





$ 





$ 







$ 


300,789 


$ 


21,139 
100,000 


$ 


321,928 
100,000 



$ 394,421 
1,958,487 



$ 
$ 

$ 
$ 



394,421 

$ 
-33,000 



•319.098 $ 
316,306 

■123,085 $ 
122.008 



$ 394,i.21 



$ 
$ 



-20,773 $ 
23.565 

-8,024 $ 
9.101 




-33.000 



171 



TABLE XLV Concluded - SCOUT - NAS1-12500 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



FUNDED 
M-39 Increase Effort - Task R $ 959,792 

M-40 Reimbursable Manhours Change-Tasks J,M 
M-41 Decreased Efforts - CR1 -1,692,000 

M-42 Decrease in Traget Price -l40,948 

CCN S-008 Fab.&Repl. Scout Fin Tools 
M-43 (Funded) E7000V - Task S 37,000 

M-44 Redetermined 



TOTAL 

(1) 
(2) 
(3) 
(^) 
(5) 
(6) 
(7) 



TARGET COST 



TARGET 
PROFIT 



TARGET 
PRICE 



$ 892,830 $ 66,962 $ 959,792 



-1 ,692,000 

-131,728 

37.000 

$ 37.000 



-9,220 



■1 ,692,000 
-140,948 

37,000 
-633,443 













$30,759,245 


$27,642, 


,186 


$3, 


,117, 


,059 


$30, 


.125, 


,802 


TASKS 


A,B,C,D,E,F 

J 

M 

R 

W 

S 

Performance 


,G,H,K, 
Award 


L,N, 


,P,T,V 


$18,199,403 
1,462,384 
1,350,244 
6,443,700 
413,129 
1,230,942 
1,026,000 


(FPI) 

(CPFF) 

(CPFF) 

(CPFF) 

(CPFF) 

(FFP) 

















TOTAL 



$30,125,802 



172 



TABLE XLVI - SCOUT NASI -131 00 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



Funded 



Total 



Contract 



2 Algol III Motors (GFP Cases) 

550if-1P17 - S-200 (Case 1013) 
550it-2Pl8 - S-198 (Case 1010) 

5 Algol I I 1 Motors 



$1,500,000 $2,9ol,i»30 

($ 3'«6.982) 

d.'* 30. 735) 



(1)550U-3P19 - Test (Case 2001) (Case refurbished on NAS1-1U200) 

5504-4P20 - S-201 (Case 2002) 

550it-5P21 - S-192 (Case 2003) 

550U-6P22 - 5-202 (Case 2005) 

5504-7P23 - S-203 (Case 2004) 

(680,000) 
(^70,070) 



10 Algol 


1 II 


Cases 




10 Algol 


II 1 


Nozzles 




Case j^ 


Scout 


Nozzle § 


2001 




S-205 


22 


2002 




S-206 


23 


2003 




S-207 


Ik 


200if 




S-208 


25 


2005 




S-210 


26 


2006 




S-212 


27 


2007 




S-21it 


28 


2008 




S-216 


29 


2009 




S-218 


30 


2010 




S-219 


31 



Igniter Components, etc. 

M-1 Spare Igniter (#00^+2) 

M-2 Change in Financial Reporting 

M-3 Change in Propel lant Requirements 

M-4 Clarification Contract Priority Rating 

M-5 Algol III Motor Tooling 

Decrease in Nozzle Materials 



M-6 Funding 

M-7 Algol III Rocket Motor Case Tunnel 
Tabs Corrections 

(1)Case refurbished on contract NASl-1'+200, 



(33,6A3) 



$ 6,279 


$ 


6.279 




$ 







$ 







$ 







(40,260) 

(-8,040) 

$ 


32,220 


$1 ,000,000 


$ 







$ 






L 



173 

TABLE XLVI Concluded - SCOUT NASI-I3IOO (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 

Funded Total 

Contract 

M-8 Reduction in Quantity of Completed $ 

Algol III Nozzles 

M-9 Funding $ 340,220 $ q 

M-10 Adjustment for Tunnel Tabs Correction (M7) ^ "3,710 

M-n Administrative Change $ 

M-12 Funding $ 1^9,720 

M-13 5 Algol III Motors ($750,8/tO) 866,564 

5504-8P24 - Unassigned (Case 2012) 
5504-9P25 - Unassigned (Case 2013) 
5504-10P26 - Unassigned (Case 2015) 
5504-11 P27 - Unassigned (Case 2014) 
5504-12P28 - Assigned S-199 (Standby) (Case 2016) 

1 Algol III Motor Case (60,064) 

1 Lot Algol III Propellant (55,660) 

M-14 Decrease in Contract Fixed Price $ -11^79 -njyg 

M-I5 Administrative Change 

M-I6 Adjustment in Contract Price $ -2,345 -2,345 



TOTAL $3,849,259 $3,849,259 



174 



TABLE XLVIi - SCOUT - NASI -1^200 (CONTRACT HISTORY) 

VOUGHT CORPORATION 

Contract for Scout Motors $1,163,000 

1 . Castor I lA (6-30-77 + 1 every three weeks) 

(a) 10 Cases (Uninsulated) $237,300 
Case #'s 1399 

1i+00 

1401 

1402 

1403 

1406 

1407 

587-08 

587-09 
587-10 

(b) 10 Nozzles (Forgings) $102,500 
Nozzle #'s: 

867-02 
867-03 
867-04 
867-06 

867-07 
867-08 
293-01 
293-02 
293-03 
293-04 

2. Antares MA (3-31-77 thru 8-31-77) 

5 Motors (Less Igniters, $258,075 

Initiators and nozzles) 

(1) Cases - GFP 

(2) Casting Powder - GFP 

(3) Cork Sheets, Silver Paint, 

Tunnel Tabs - GFP 
Motor #'s: 410 S-205 (GFE Case 204) 
411 S-201 (GFE Case 205) 
kM S-202 (GFE Case 206) 

413 S-204 (GFE Case 212) 

414 Unassigned (GFE Case 214) 

3. Altair MIA (6-30-77 thru 12-31-77) 

(a) 6 Motors (Less Initiators) $558,690 

(1) Pole Fittings - GFP 

(2) 3 Cases - GFP (028, 029, 030) 

(3) Initiators - GFP 



175 



TABLE XLVII Continued 



SCOUT - NAS1-14200 (CONTRACT HISTORY) 
VOUGHT CORPORATION 



3. 



M-3 



H-k 



M-5 



cont inued 
(a) continued 

Motor #' s: 
E23 S-201 (Case 032, Nozzle 103, 
NRL (Case 033, Nozzle 104, 
S-192 (Case 034, Nozzle 101, 
S-198 (Case 028, Nozzle 107, 
NRL (Case 029, Nozzle 108, 



E24 
E25 
E29 
E30 
E31 



Igniter 037) 
Igniter 038) 
Igniter 039) 
Igniter 02 7) 
Igniter 029) 



Unassigned (Case 030, Nozzle 109, Igniter 035) 



$ 6.435 



(b) 3 Igniters 
M-1 Antares I lA Motor 

1 Motor (Less Igniters, Initiators 

and Nozzles) 
415 Assigned S-199 (GFE Case 215) 

M-2 Altair I ||A Motor 



3 Motors with Nozzles and Igniters 

Less Initiators ($118 245) 

E26 S-203 (Case 036, Nozzle 106, Igniter 032)* 
E27 S-202 (Case 037, Nozzle 105, Igniter 034) 
E28 AEDC Test (Case 038, Nozzle 102, Igniter 036) 

12 Exit Cone and Flange Assemblies, ($134,400) 
and 12 Nozzle Throat Insulators 

2 Core Covers, Repair of 1 Core Cover 
(Antares II) 



Altair I I lA Motors 

2 Motors with Igniters and GFE Nozzles 
Less Initiators 
E32 Assigned 199 (Standby) 

(Case 039, Nozzle 110, Igniter 04l 
E33 Unassigned (Case 040, Nozzle 111, Ignhsr 
4 Motors with Nozzles and Igniters 
E34 NRL (Case 044, Nozzle 014, Igniter 046) 
E36 NRL (Case 043 , Nozzle 004, Igniter 048) 
E37 NRL (Case 042, Nozzle II3, Igniter 045) 
E38 Unassigned (Case 041 , Nozzle 112, Igniter 



($149,052) 



043) 



112) 



ir.i tiators($l,540,374) 



11 Antares I I I Motors 

II AriLares ill Motors Less 

4 Antares I II Cases ($ 

4 Antares I I I Nozzles ($ 

Antares III Igniter Hardware ($ 

Antares III Igniter, Less Initiators ($ 



(b) 
(c) 
(d) 
(e) 



159,716) 

142,736) 

15,055) 

7,902) 



$ 40,629 



$ 261 ,645 



$ 1,080 



$ 683,734 



$1,865,783 



176 



TABLE XLVII Continued - SCOUT 



NASI -14200 (CONTRACT HISTORY) 
VOUGHT CORPORATION 



■5 Continued 

Motor #' 

E-2 

E-3 

E-k 

E-5 

E-6 

E-7 

E-8 

E-9 

E-10 

E-11 

E-12 



M-6 



M-7 



M-9 
M-10 



Unass igned 
Unass igned 
Unassigned 
Ass igned 
Ass igned 
Ass igned 
Ass i gned 
Ass igned 
Ass igned 
Ass igned 
Ass igned 



(Case 014)(S-192) 
(Case 016) 
(Case 017) 



Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 



Vll 
VI i 
Vll 
Vll 
Vll 
VI I 
VI I 
Vll 



(Case 018) 

(Case 020) 

(Case 021) 

(Case 022) 

(Case 023) 

(Case 019) 

(Case 024) 

(Case 015) 



10 Castor I lA Motors 

4 Castor I lA Motors with Igniters 

Less Initiators, with Case and Nozzle 

6 Castor MA Motors with Igniters 

Less initiators, with Case and 

Nozzle Forg ing 

1 Castor MA Shelf-Life Program and Report 

signed (GFP Case 911) 
signed (GFP Case 913) 
gned S-199 (Standby) (GFP Case 914) 



Motor #'s 



($488,328) 
($913,080) 

($ 55,015) 



$1,456,423 



808 
809 
810 
811 
812 
813 
814 

815 
816 

817 



Unas 
Unas 
Ass i 
Ass i 
Ass i 
Assi 
Ass i 
Ass i 
Assi 
Assi 



gned 
gned 
gned 
gned 
gned 
gned 
gned 



Phase 
Phase 
Phase 
Phase 
Phase 
Phase 
Phase 



VI 
VI 
VI 
VI 
VI 
VI 
VI 



(Case 1399) 

(Case 1400) 

(Case 1401) 

(Case 1402) 

(Case 1403) 

(Case 1406) 

(Case 1407) 



Altair III Rocket Motor with Igniter 

and Government-furnished Nozzle (Line Loss Motor) 
Motor # E35 (Case 046, Nozzle 114, Igniter 047) 



$ 40,559 



M-8 Castor MA Tests (See Mod. 13) 



Additional Testing & Inspection for Castor MA Motor Product ion(See Mod. 13) 



10 Algol MIA Motors (Cases GFP) 

(a) 2 Algol IMA Motors Less Initiators 

with Case, Nozzle, and Polymer 
S/N 5505-1 (Case GFP 0001) 
S/N 5505-2 (Case GFP 2001) 

(b) 3 Algol MIA Motors with Case, Igniter, 

Nozzle, and Polymer, Less Initiators 
S/N 5505-3 (Case GFP 0005) 
S/N 5505-4 (CASE GFP 1001) 
S/N 5505-5 (Case GFP 2007) 



($443,312) 



($608,127) 



$2,216,445 



177 



TABLE XLVII Continued - SCOUT 



M-10 Continued 



NASI -1^*200 (CONTRACT HISTORY) 
VOUGHT CORPORATION 



M-13 
M-14 



M-15 
M-16 

M-17 



(d) 



(c) 1 Algol MIA Motor with Case, Nozzle, 

Igniter, and Polymer, Less Initiator 
S/N 5505-6 (Case GFP 2008) 
k Algol IMA Motors with Case, Nozzle, 

Igniter, and Polymer, Less Initiators 

S/N 5505-7 (Case GFP 2009) 

5505-8 (Case GFP 2010) 

5505-9 (Case GFP 2011) 

5505-10(Case GFP 2006) 

Algol IMA Motor Igniter, with Igniter 

Components and Polymer, Less Initiators 
Algol IMA Motor Igniter, With Polymer, 

Less Initiators 
PBAN Polymer, Less I n i t iators (GFP Cases) 



($19^,010) 



($779,616) 



(e) 
(f) 

(g) 



S/N 5505-1 
5505-1 
5505-1 
5505-1 
5505-1 
5505-1 
5505-1 
5505-1 
5505-1 
5505-1 



-1 

-2, 

-3. 

-^, 

-5, 

-6, 

-7, 

-8, 

-9, 



Phase VI I 
Phase VI I 
Phase VI I 
Phase VI I 
Phase VI I 
Phase VI I 
Phase VI I 
Phase VI I 
Phase VI I 



-10, Phase VI I 



(Nozzle 036) 

(Nozzle 038) 

(Nozzle 035) 

(Nozzle 037) 

(Nozzle 034) 

(Nozzle Oil) 

(Nozzle 39M) 

(Nozzle kOH) 

(Nozzle k^H) 

(Nozzle 42M) 



($ 4,171) 
($ 51,716) 
($135,493) 



M-11 Substituting Kentron International, Inc., for Vought Corporation 
M-12 Change to Antares I lA Motor Specifications 



Castor MA Motor lesting and Inspection (Mods 8 and 9) 



4 Castor I lA 

S/N IIA-818, 

MA-8I9, 

I IA-820, 

IIA-821 , 



Motors 
Phase VIII 
Phase VI 11 
Phase VIII 
Phase VIII 



(Case 587-08) 

(Case 587-09) 

(Case 587-10) 

(Case 587-11) 



$ 50,418 
$ 748,064 



Clarification of M-14 Changes 

Contract Schedule Changes 

2 Additional Antares MIA Motors, Less Initors 
S/N E-13 
E-14 



$ 258,510 
$ 181,547 



M-18 Procurement Additional Altair IMA Fourth-Stage Motors $1,310,039 
M-I9 Contract Schedule Change $ 



178 



TABLE XLVil Concluded - SCOUT - NAS1-14200 (CONTRACT HISTORY) 

VOUGHT CORPORATION 

M-20 2 Additional Altair MIA Igniters and Antares MIA $ 256,600 

Motors, and 1 Additional Antares III Igniter 

S/N E-15 
E-16 

M-21 Additional Altair I I |A Rocket Motor $ 101,505 

S/N E5^ 

M-22 Description Change on Contract Schedule $ 

M-23 Specification Change to Include 2 Lots of PBAN instead $ 
of 1 



TOTAL 



$10,635,981 



TABLE XLVIII - SCOUT - NASl-15000 (CONTRACT HISTORY) 
LTV AEROSPACE CORPORATION 



FUNDED 



TASK _^ 

A Program Management 

C Pref 1 ight Planning 

D Data Reduction/Analysis 

E Systems Engineering 

F Rel iabil i ty 

G Standardization & configuration Control 

H Vehicle Processing 

L Logistics Support Management 

N Field Services 

P Langley Support 

T Support to Production 

V STE/Tool Maintenance 

TOTAL 

W Incentive 

CONTRACT $3,350,0 





TARGET 


TARGET 


TARGET COST 


PROFIT 


PRICE 


%k,m,shi 


$373,755 


$4,651,297 


166,297 


14,531 


180,828 


330,835 


28,907 


359,742 


1,649,821 


144,155 


1,793,976 


2,0i»7,759 


178,925 


2,226,684 


848,956 


74,179 


923.135 


1,799,280 


157,214 


1.956.494 


788,663 


68,911 


857.574 


5.795,953 


506,428 


6,302,381 


726,743 


63,500 


790,243 


901,537 


73,773 


980,310 


866,614 


75,722 


942,336 


$20,200,000 


$1,765,000 


$21,965,000 




$600,000 


$600,000 


$20,200,000 


$2,365,000 


$22,565,000 



179 



TABLE XLVIII Continued - SCOUT - NASI -15000 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

M-1 
M-2 



FUNDED 



TARGET 
TARGET COST PROF I T 



$4,0if6,000 



M-3 
M-4 



Schedule Change 

Funding-Tasks C,D,E,F, 
G,H,L,N,P,T,V 
E7000E.F,G,H,L,P,T,V 
E7002N, 7200H,7201C,D,N 

Retransfer Contractor 
Personnel-Task N-E7000N 

Add - Task Y 

5 Scout Vehicles ($4,099,634) 

6 Heat Shields - 34"-40 ($422,943) 
2 Heat Shields 42"-45 ($182,554) 

5 Series 25 Separation Systems ($181,554) 
1 Base-A Cable (S207) ($6,868) 
1 Set S^ET Components ($113,671) 
1 60-lb. Motor Chamber (S207) ($1 ,921 ) 
40 Weights ($5,806) 



$ 
$ 



$ 
$ 








$ 

$ 



$ 95,000 $ 95,000 $ 



M-5 
M-6 
M-7 
M-8 
M-9 

M-10 



$ 4,517,568 $ 496,932 



Administrative Change 

Fund ing 

Fund ing 

Cost Reporting Change 



$ 



$2,804,000 $ 

$4,500,000 $ 

$ 



Production Support, 5 Vehicles, Task T $ 
E8000T, E8002T 

Production Support, $ 

6 Altair MIA, Task T, 
E8000T, E8002T 



$ 

$ 

$ 

$ 

$ 

$ 











Accommodate Phase VII Guidance 
System 



TARGET 
PRICE 






95,000 
$ 5,014,500 











M-11 


Guidance System 




$ 


6,079, 


,000 


$ 


390, 


,000 


$ 


6,469,000 


M-1 2 


Administrative Change 




$ 







$ 







$ 





M-1 3 


Production Support (5 Veh.) 
(Mods 8 & 9) 




$ 


320, 


,229 


$ 


35, 


,225 


$ 


355,454 


M-14 


Delete 2 Heat Shields 




$ 


-164. 


,057 


$ 


-18, 


,046 


$ 


-182,103 


M-1 5 


Funding 


$9,300,000 


$ 







$ 







$ 





M-16 


Production Support, Antares 
Rocket Motor, Task T,E7000T, 


IMA 
E7002T 


$ 







$ 







$ 





M-1 7 


Production Support for Castor 1 |A, 
Task T 


$ 







$ 







$ 





M-1 8 


Reconfigure Phase VIM Vehic 


les to 


$ 







$ 







^ 






180 



TABLE XLVIII Continued - SCOUT - NASl-15000 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



■TASK 
M-19 

M-20 
M-21 

M-22 
M-23 

H-Zh 

M-25 
M-26 

M-27 

M-28 

M-29 
M-30 
M-31 
M-33 
M-3^ 



FUNDED 



Production Support (Mods 17 & 18) 
M-17 - $89,320 
M-18 - $48,580 

Storage of Guidance System 
Components in GFE Stores 

Task J, San Marco Support 

Task M, Logistics Support Mat' Is 

Task R, Program Support 



Funding 



$10,000,000 



Transfer of Money from 
Task R, Special Programs, 
to Task M, Logistics Support, 
Materials 

Transfer of spares inventory 
from contract NASI -151 00 

Period of Performance Ext. $ 

Funding $3,200,000 

Add 5 ITV Scouts, Task Y 
Incent ive, Task W 

Funding Correction $ 

Task T, Production Support $ 

Retransfer of Personnel $ 61,400 

Task T, Production Support $ 

Task S, Program Support $ 



TARGET COST 



TARGET 

PROFIT 

.1 



TARGET 
PRICE 



$ 137.900 $ 15,169 $ 153,070 

$ 97,426 $ 8,196 $ 105,621 

$5,923,011" $ 444,230" $6,367,241 

$ $ $ 

$ $ $ 



$ 



$ 



$14,771,000 $1,290,542 $16,061,542 

$ $ $ 

$3,854,000 $ 423,940 $4,277,940 

400,000 400,000 



$ $ 
$ $ 
$ 61 ,400 $ 









$ 
$ 
$ 61.400 



$ 228,324 $ 25,116 $ 253,440 



Funding 



$13,461 ,000 



$ 
^ 



$ 








^ Cost Reimbursable. 



181 



TABLE XLVIII Concluded - SCOUT - NASI -1 5000 (CONTRACT HISTORY) 

LTV AEROSPACE CORPORATION 



TASK 

M-35 ^th Stage T/M- Ignition 

Hardware (I TV Procurement) $ 

M-36 Task S, Program Support 
(CCN-001) 

M-37 Change in Billing Sched. 

M-38 Transfer of Funds 
(Task M and R) 

M-39 Task S, Program Support 
(CCN-002) 

H-kO Funding 

M-41 Delivery Schedule Change 

H-k2 Completion Date Change 
(CCN S-002) 

M-^3 Billing Schedule Change 

H-kk Funding 

TOTAL CONTRACT 
**Firm Fixed Price. 



FUNDED 


TARGET 


COST 


TARGET 
PROFIT 






TARGET 
PRICE 


0$ 


.$ 







$ 





$ 





$ 73.787"" 


$ 


73 


,787 


$ 





$ 


73,787 


$ 


$ 







$ 





$ 





$ 


$ 







$ 





$ 





$ 176,533'''' 


$ 


176,533 


$ 





$ 


176,533 


$5,839,000 


$ 







$ 





$ 





$ 


$ 







$ 





$ 





$ 


$ 







$ 





$ 





$ 


$ 







$ 





$ 





$1,784,000 


$ 







$ 





$ 





$58,690,720 


$56,371 


,121 


$5,875,304 


$62,247,425 



182 



TABLE XLIX - CONTRACT NASI-I5IOO, TASK R SPECIAL STUDIES 



TASK 
NO. 

1 
2 
3 



5 
6 
7 
8 

9 
n 

12 

13 
14 

15 

16 

17 

18 

19 

21 

22 

2k 

25 

27 

28 

29 

30 

31 

32 

33 

34 

36 

37 

38 
39 

40 
41 
42 

43 
44 



Prog, 



DESCRIPTION 

General Mission Integration 
Salvage Antares MB Nozzle Cones 
Rewrite of Vol. VII SOP, Standard 

Countdown Manual 
Phase VIM Guidance Systems and 

Telemetry Test Philosophy 
Dynamic Analysis, HCMM 
Algol I I lA Static Test 
Ultrasonic Inspection Training 
TRANSAT Spacecraft Design Tasks 
HCMM Spacecraft Design Tasks 
TRANSAT Heat Shield Mod. & Fit Check 
Phase VIM Engineering Changes 
Clean Room at WFC 

Vehicle S-200 Fourth-Stage T/M Mod. 
Testing of Phase VII Components to 

Apol lo Test Levels 
X-258 Motor Shelf Life Program 
Design & Fabricate Miscellaneous GSE 
PCM Telemetry Pkg. Development 
X-258 & X-259 Igniter Shlf.Lf.Anal 
Rev. Std. Handling Manual for NAD 
Heat Shield Rework 
Scout Guid.Sys. Integration 
Scout Users Manual Revision 
N2 Regulator & Shut-off Valv Eval. 
Base A Algol Ml Seal Installation 
Performance & Trajectory Rept. Update 
Base A Battery Terminal Replacement 
Historical Summary Report Update 
Scout Software Development Center 
Fourth-Stage Dynamic Balance Study 
34-25 inch H/S Extension Study 
Simulated Payload Stiffening Structure 
GSE Changes to S-208 & Sub., Ignition/ 

Destruct. Sys. 
Design for Adapting 25 Series E Sects. 

Clamp to 200 Series E Sections 
Reconfig. TX-354-5 to TX-354-3 Castor 

Motors 
S-198 Command Destruct Receiver Repl . 
HCMM Spacecraft Related Effort 
Fourth-Stage Instrumental ion/ Ign i t ion 

System, S-201 
X-258 Nozzle Examination 
Design, Dev., &Qual. Antares III Mtr. 



J.O. (E) COST 



MA 



7OOOB $ 

7OOOZ 

7OOOG 

8003Y 

7201 B 
7OOOF 
7OOOK 
72OOB 
7201 B 
72OOH 
8OOOE 
70000 
72OOY 

7OOOF 

7002R 

70000 

8OOOR 

7000R-7002R 

7OOOG 

7002H-7199H 

8003Y 

7OOOB 

7OOOF 

8OOOY 

7OOOD 

7OOOY 

7OOOD 

8003Y 

7OOOG 

8OOOR 

7OOOV 

80000 

7OOOR 
7005Z 

7I98Y 
7201 H 



174,204 $ 
43,001 
18,873 

^7,099 

13.013 
16,158 

4.817 

7.131 
11,687 
50,578 
12,162 

1,378 
17,323 

82,122 
23,148 
45,671 
146,733 
7,957 
12,648 
7.334 
700,674 
15,289 
30.321 
17,070 
22,731 
3.361 
18,467 
21 ,659 
53,833 
18,357 
7,356 

37.412 

18,865 
39,796 

14.336 
47,865 



TOTAL/ 
W/PROFIT 

189,185 

46,699 
20,496 

51,149 

14,132 

17,548 

5,231 

7,744 

12,691 

54,928 

13.208 

1.497 

18,813 

89,184 
25,139 
49,599 

159,352 

8,641 

13,736 

7.964 

760,930 
16,604 
32,929 
18,536 
24,686 
3,650 

20,055 
23.522 
58,463 
19.936 
7.989 

40,629 

20,487 
43,218 

15,569 
51.981 



720IJ 22,652 24,600 

7002R 55,873 60,679 

8003Z 2,821.743 3.064,409 



183 



TABLE XLIX - CONTRACT NASl-15100, TASK R SPECIAL STUDIES, 



TASK 
NO. 

45 

hi 

48 

49 

50 

51 

52 

53 

54 

55 

57 

58 

59 

61 

62 

63 

64 

65 

66 

67 

68 

69 

70 

71 

72 

73 

74 

75 
76 

n 

78 
79 
80 
81 

83 
84 
85 
86 

87 

88 

89 

90 

91 

92 



DESCRIPTION 

Support Antares III Des., Dev., Qual. 

& Incorp. into Scout Vehicle 
Scout/TDRSS Compatibility Interface Stdy 
Scout Pay load Weight Capability 
Film Progress Report 
Scout PCM Telemetry Integration 
Scout PCM Telemetry GSE integration 
Scout Guidance System Integration 
Guidance System GSE Integration 
Third-Stage Coast Disturbance 
Altair I I I Static Test Firing 
Qual. Marotta Regulator Design Imp. 
E-Section Clamp Prestra in/Loads Test 
Data Collection Satellite Sys. Study 
X-259 Nozzle Evaluation 
Furnishing Manufacturing Engineering 
incorp. Altair I ||A in S-199 
Printing of Scout User's Manual 
Analysis & Des. 34", -55 Heat Shield 
S-192 Fourth-Stage Instrumentation 
Castor MA Ultrasonic Equipment 
Feasbity. of Extending 42" Dia. H/S 
Procurement of Graphite G-90 
Ultrasonic Inspection Rkt.Mtr .Recert . 
Updated Scout Fluids Design Data 

Mfg.sQual. Series 200 Sep, Sys .Clamp 
P/L Sep. Nuts & Attach Rings 

Work Breakdown Struct. Changes, 
Phase VI I I Vehicles 

S-199 Special Fourth-Stage Instruments 

SAGE Spacecraft Design Tasks 

Battery Processing 

Delta Postflight Data Reduction, S200 

Antares III Incorporation into S-203 

S-207 Modifications 

Fab.s- Test Roll & Yaw Compensation Units 

Rework GFE Roll/Yaw Compensation Units 71 

Review Radiographic Inspections 

Scout Payload Scale Models 

Algol I IC Igniter Shelf Life 

Balance Middle D-Section 

Antares Ml G-90 Graph i te Test ing 

Payload Fnv i ronmenta 1 Control System 

Antares III Retainer Rings Test' 

S-207 From Storage 

MAGSAT Design 



8003Z 
. 8000R 
7000D 
7000D 
8000R 
8000R 
8003Y 
8003Y 
7000W 
8000R 
7000F 
7198R 
8000D 
7000W 
8000E 
7199B.H 
7000B 

8003R 

6192R 

70000 

8003R 

8003Z 

7000K 

7000E 

7000R 

7198Y 



Cont inued 



COST 



8000A 
7199H 
7202B 
8000K 
7200D 
7203R 
720 7H 
7000Y 
99H-6192H 
7000F 
70000 
7002R 
7000R 
8003 Z 
70000 
8003Z 
720 7H 
7203B 



841 ,025 

13,767 

5,309 

44,015 

26,289 

260,517 

199,552 

421 ,484 

73,962 

6,052 
52,539 
50,899 

8,422 
51,226 
31.928 
41 ,201 

2,014 
43 , 1 70 
20,262 

1,790 

17,767 
26,202 
17,472 
4,831 
174,957 
62,504 

14,442 
30,936 
18,870 

3,545 

6,008 
77,185 
26,730 
67,168 
36,670 

9,688 
20,378 

9,721 

10,596 

27,775 
1 7,020 

21 [772 
28,996 

26,259 



TOTAL/ 
W/ PROF IT 



913,352 

14,953 

5,766 

47,800 

28,550 

282,921 

216,713 

457,731 

80,323 

6,574 

57,057 
55,276 

9,146 
55,631 
34,674 
44,745 

2,187 
46,883 
22,005 

1,944 
19,295 
28,i+56 

18,975 

5,246 

190,003 

67,879 

15,684 
33,596 
20,494 
3,850 
6,525 
83,823 
29,028 
72,944 
39,822 
10,521 
22,131 
10,557 
11.507 
30,164 
13 ZiS'j 

23 ,'644 
31.490 

28,517 



184 



TABLE XL{X - CONTRACT NASI -151 00, TASK R SPECIAL STUDIES, Concluded 

TASK 
NO. DESCRIPTION 

93 Algol I 11 SN5504-4 

Sk SAGE Effort 

95 Altair IMA Propel lant Test 

97 Review Altair I I lA Rad iographs 

98 Homogenity Study, Altair ill Propellant 

99 Aging Study Report-Scout Motors 

100 Servo Actuator Acceptance Test Box Mod. 

101 Radiographic Inspect., Algol III Motors 

102 Revision SOP 

103 Reprogram Contractor Report (SPAC) 

104 Algol lie Motor Shelf Life 

105 Antares III Special Instrumentation 

106 Replacement of Fin Meters 

107 Furnish & Test ATJ-S Graphi te, Antares III 

108 Post-Cure of Phase VIM H2O2 Bladders 

109 Update of Design Data Reports 

110 S^ET Rate Gyro Unit & Body Bending Fltr. 

111 NOVA- 1 Pre! iminary Trajectory 6l92B,H,82l 

112 Technical Changes to Scout SOP's 

113 Review of Vendor Supplier Fab. Processing 

114 UK-6 Spacecraft Umbilical Design 

115 Processing Bladders and H2O2 Tanks, S-207 

116 DITTO for S-199 

117 MAGSAT Heat-Shield Mods, A-41 2 

118 Nozzle Materials Study 

119 Bladder, Adhesion, Processing H202 Tanks 

and F i 1 ters 

120 Algol lie Shelf Life Ext.& Flight Test. 

121 Altair IMA Exit Cone Investigation 

122 Documentation of Phase VII Drawings 

123 Silver Zinc Battery Cell Development 

124 Scout MAGSAT Telemetry Interface 

125 Fabrication of UK-6 Umbilical Cable 

126 Scout Standard Cyclic Life Test, Phase 

V I II Components 

127 UK-6 Add Access Door to Dummy Heat Shield 7198O 

128 Fourth-Stage Instrumentation, S-203 

129 Scout Standard Environmental Test 
132 Ultrasonic Inspection, Recert. Field Prsnl 



J.O. (E) 


COST 


W/ PROF IT 


7OOOF $ 


3.452 $ 


3,749 


7202H 


59,558 


64,680 


8000Z 


15,642 


16,986 


8OOOF 


3,188 


3,462 


8003Z 


6,470 


7,026 


8003Z 


46,668 


50,681 


7OOOF 


4,554 


4,946 


7OOOF 


14,449 


15,692 


7OOOG 


1 2 , 1 09 


13.150 


7OOOA 


3,211 


3,487 


7002R 


44,039 


47,826 


8003Z 


58,037 


63,028 


70000 


12,424 


13,492 


8003Z 


5,184 


5.630 


8005Y 


58,736 


63.786 


7OOOE 


16,510 


17,930 


7OOOR 


16.852 


18,301 


8b,H,8210B 


96.729 


105.027 


7OOOG 


9.368 


10,174 


8000F 


81.972 


89,018 


71 98b 


7.988 


8,675 


7207H 


17,925 


19,467 


7199H 


12,063 


13,100 


7203H 


55.809 


60,608 


7OOOR 


17,070 


18,538 


6192H 








18,177 


19,740 


7OOOR 


98,378 


106,838 


7OOOR 


2,625 


2,851 


7OOOE 


13,368 


14,518 


7OOOR 


10,615 


n.528 


7203J 


8,725 


9.475 


7198H 


2,413 


2,621 


8002F,8005F 








80,604 


87,536 


71980 


3.029 


3,289 


72 03 J 


31,329 


34,023 


7OOOF 


10,241 


11,122 


.7OOOK 


3,445 


3.741 



I 



185 

VEHICLE PRnrilRFMFKiT 



The Scout hardware cont-rari-e f fm. 

XXXV,. Although an the ^5plZe7lV,\cTet ''^"^/^'^^ '" "^^^'es XXX.,, and 

the^jeat sh.e.ds varied. ^oUo.^^^' ^^;:^--Z^-^l^[^^^^.S^^^ 

8? ?^/-25 A60 NAS-7qq NAS1-12500 

IrI ^V-""^ A504 ^S -693? 41 NAS1-10000 

8? ^y-'^^ A^O^ MAS -693^4 NASI -10000 

84 ^y-'5 A63 MAS -7?9Q NASl-10000 

S ^y-'^^ A402 NAS-69??4I ^ASI-IOOOO 

86 ^^/-'^^ A403 NAS -69?r4 NAS1-10000 

o ^2/-45 A507 MAC ^?^^", NASl-10000 

187 42/-45 MOq ^^t^i^^^■^^ NASl-10000 

'?^ ^2/-45 JboI kTc I^^^-"^^ NASl-10000 

'^^ 3V-40 A406 T^.\~^^.^-)' NASl-10000 

^ 3V-40 A4oq Tc ;I^^ , NASl-10000 

^'^ 3V-40 ,1?? A Ik^o'^ ^^^^-^°°°° 

NAbl-15000 NASI -15000 

The Separation systems used in Pha^^ ui 

-nformation for each Phase V, vehicle Li Llf'"'^!'' '^°^'""9 ^^^ ^°"tract 
system: venicie equipped with a Scout separation 

Vehicl e No. Tvoe c • , . 

-1XH£ Sena No. T^cf- nr,:*- m 

ii^'t No^ Contract No. 

NASI -6935 
NASI -7256 
NASI -6935 
NASI -7256 
NASI -72 56 
NASl-10000 
NASI -7256 
NASl-10000 
NASl-10000 



180 


■ / 

F 


181 


E 


183 


E 


185 


E 


186 


E 


187 


E 


188 


E 


189 


E 


191 


E 



36 


25 


46 




31 


27 


45 


32-44 


hS 




l^h 


203 


48 


47-50 


206 


202 


102 


101 



186 



MOTOR PROCUREMENT 



Table XXXV itemizes the contracts that supplied tiie motors for the Phase Vl 
vehicles. It should be noted that NASl-7199 was the major hardware contract for 
Phase VI, however contracts NAS1-5610, NASl-SSSS^'^ NASI -7102(2) , NASl-9258, 
NAS1-11400, NAS1-13100(3) , and NAS1-14200 also included Phase VI motors. 
The motors of Phase VI were all solid propel lant and contracted as follows: 



Quant i ty 



Stage 



NASA Contract 



6 


Algol lie 


NASl-7199 


8 


Algol III 


NASl-9258 


1 


Algol Mi 


NASI-I3IOO 


14 


Castor MA 


NASl-7199 


1 


Castor 1 lA 


NAS1-11400 


12 


Antares 1 lA 


NASl-7199 


1 


Antares 1 lA 


NAS1-11400 


1 


Antares MB 


NASI -11400 


1 


Antares i lA 


NAS1-14200 


3 


Altair M lA 


NASI-56IO 


1 


Altair MA 


NASI -5883 


7 


Altair MIA 


NASl-7199 


3 


Altair IMA 


NAS1-11400 


1 


Altair 1 MA 


NASI -14200 


1 


Alcyone 


NASI -71 02 



Although most of the few Scout failures were due to propulsion, there were 
not any Scout Phase VI failures of any kind. It was the only 100 percent 
successful phase to date. 

The propulsion procurement staff not only contracted for the aforementioned 
motors, but the NASA contracts also included the following additional flight 
hardware: 

Motor Initiators 

Motor Ign i ters 

Motor Casting Powder'^' 

Squib Reta iners 

SBASI 

Motor Nozzles 

Motor Nozzle Inserts 



(1)nAS1-5883 contract included the only X258 motor in Phase VI, expended on 

vehicle S-1 78. 
(2)nAS1-7102 contract was for BE-3 fifth-stage motors used only on S-I9I. 

(3)nAS1-13100 contract was for Phase VII Algol III motors with the exception 
of one first-stage motor for S-192. 

'^^The motor Casting powder was procured independent of the motor for the 
th i rd stage on iy . 



187 



Motor Tool ing 
Motor Cases 
Motor Spares 
Safe Arm Units 
Explosive Bolts^n 
Spin Motors 

New Motor Developments 
Refurbishing Tooling 
Motor Inspection 
Storage Requirements 
Technical Support 
NOT Techniques 
Quality Control Program 
Qual ity Tests 
Leak Tests 
Hydrotest Cases 

Flightworthiness Studies 

Static Tests 

Ground Support Equipment 

Motor Spares Administration 

Storage Facility Repairs 

Motor Dol 1 ies 

Motor Instrumentation 

Anomaly Studies 

Failure Investigations 

Propulsion Ground Support Equipment 

Lase Cleaning 

Shelf Life Studies and Tests 

Packaging 

Pro^r ™';:.:i\^';:-4^:/-^ -d .e.e,o^e„t -t.ac. of t.e Scout 

NAS1-10485 - Alonl M A 

NASI -10484 - A CO ," u'Tl '^""''"' Corporation (2) 

NASl-10482 - Castor Thik"''r ^"^^"°'°9y Corporation 

NAS1.10483 - An ares")} Th- ?,''7'"'^''°^ 

NASl-10481 - X ?%!,!•" °^°' Corporation 

NASI- otsi - FW4S AI at;' 'u'^'^'^' Incorporated 

NAS1-7102 - Be!?3 F^ th StLe n '/'''"°'°^^ Corporation 

NAS1-8994 - NDT study '' ^^elopment 

NASI -11867 - NDT Study 



OJExplosive bolts were used for stage seoarat ion 

'^)Co..c. .3 oe,oHa.. en. .t .'p. ^ZZ'^^ „3s „„e. .e,..e.. 



188 



The one and only five-stage Scout "E" had special contractual requirements 
n^ K!:.L'ri°l r:!'T i" 'l^^^^ ''■ ^'9-- ^9 inustrates :Se S^o^t 



IICM 



and the BE-3A9 fifth-stage motor (detailed in figure 70). 

The basic -G" section was composed of a conical magnesium adapter and separa- 
tion clamp. The 3.07-pound -G" section is designed for spacecraft which do 
not require separation from the expended fifth stage. When separation of the 
bourrn !^^^^;;"■^^ ^^^ the fifth stage, springs, plungers' pyrotechnic 
bolts and wiring harness are combined with section "G" to form the fifth 
stage separation system. The separation signal is initiated from the fifth- 
stage ignition system in the upper "F- 3.48-pound section. When the telem- 
etry system is required, a transmitter, sub-carrier oscillators and a 
battery are added to the "G" section, which is used simultaneously with the 
beacon telesponder system. ^ 

ROCKET MOTOR SHELF LIFE PROGRAM 

The VrlZnV\"^^Vll'^" °^ ''" '"°'' ^°"^"^ '"^^^^ ^^'■'^^ ^'th each motor. 
The present shelf l,fe status of existing Scout rocket motors is presented 

thVlirstatus'"^^' ^'^'^ ^'°"^ '''' ''''^'' 71(b) 1977 status.'anrmc) 

Individual studies have been conducted in the past to upgrade the motor 
shelf life to the present limits shown. However, in order to provide a 
lu'h'n h ';j'"?,'"°t°''^ presently in inventory, which will exceed the estab- 
auant;^?^ • ^ '. ^o allow the procurement of motors in more economical 
T,T/T'J '^des.rable that the shelf life of Scout motors be estab- 
lished at the maximum practical limit. Based on predicted launch schedules 
and projected motor deliveries, a shelf life goal of ten years was estab- 
lished for the Scout motors. 

discussed^below ^'°^°^^'^ Programs for the Scout rocket motors are individually 

.„^, t^rlnn ' "^ i'"''^"'"^ ^^^ •" Currently a shelf life test program under 
NAS1-15000 IS underway. This program is intended to verify the existing 

5 years limit as well as provide predictable data for increasing the life to 
10 years. The test program consists of performing laboratory tests, every 

6 months, for three years and includes propel lant tests as well as bond in 
tension samples of the case, insulation, liner and propellant system. In 
l.Z T/ f u^"^" similarities between the FW-4s motors and the Algol Ml 
Alaol M^h I ,T "\^~^' shelf life test data to confirm increased 

A go IN shelf life. The same conditions exist for the igniter Its desian 
similarity with the FW-4S igniter has allowed the use of pas^ ::;t data ^ J 

LI. I t '"^T'^ 's currently under consideration. Actual flight tests 

have been observed on a M-b-month old motor. 



189 



ORIGINAL PAGE IS 
OF POOR QUALITY 




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190 




ORIGINAL Pf^J^ 
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ORIGfNAL PAGE fS 
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192 



MOTOR SHELFUFE SUMMARY 



.-." EfS 



OF POOR QUALITY 



MOTOR 


SHELFLIFEIYRSI 


REMARKS 


PRESENT 


TARGET 


• ALGOL II 


5 


8 


MOTOR S/N 70 HAS BEEN SET ASIDE FOR STATIC FIRING 
IN 1975 


• ALGOL III 


3 


5 


LAB TESTING BEING CONDUCTED AT 6 MOS. INTERVALS 
TO 3 YEARS 


• CASTOR II 


5 


6 


MOTOR S/N 177 HAS BEEN SET ASIDE FOR SHELFLIFE 
TESTING. LAB TESTING OF PROPELLANT AND BOND 
SYSTEM INITIATED IN 1972 


• X 258 


6 


7 


X-258 STATIC FIRED IN OVER-TEST CONDITIONS FOLLOW 

ING TEMPERATURE CYCLE AND INSPECTION. 

EPON 946 LAB TESTING TO BE DONE 

INHIBITOR BOOT LAB TESTING TO BE DONE 

(21 X 259 MOTORS STATIC FIRED AT HIGH PRESSURE - DEC 72 


• X 259 


5 


7 


• BE 3 


3 


8 


PROGRAM INITIATED WITH OBJECTIVE OF 8 YEARS 


• ALTAIR III 


5 


E 


LAB TESTING OF 7 YEAR OLD MATERIALS COMPLETED 
LAB TESTING OF SYSTEM TO 6 YEARS REQUIRED WITH NEW 
VENDOR 



Ficjure 71(a)-- 1973 Status. 



MOTOR SHELFLIFE SUMMARY 



MOTOR 


SHELFLIFE (YRS.I 


BASIS FOR PRESENT SHELFLIFE 


PRESENT 


TARGET' 


• ALGOL lie 


8 


10 


OLDEST FLOWN 79 MOS. MATERIAL AND 
BONOLINE TESTING/ANALYSIS. •• 


• ALGOL IMA 


5 


10 


OLDEST FLOWN 31 MOS. MATERIAL AND 
BONDLINE TESTING/ANALYSIS. " 


• CASTOR IIA 


7 


10 


OLDEST FLOWN.82 MOS. MATERIAL AND 
BONDLINE TESTING/ANALYSIS. " 


• ANTARES IIA 


9 


10 


OLDEST TESTED.12S MOS. MATERIAL AND 
BONDLINE TESTING/ANALYSIS. 


• ALTAIR IMA 


5 


10 


OLDEST FLOWN.34 MOS. MATERIAL AND 
BONDLINE TESTING/ANALYSIS. •• 


• BE-3 


8 


10 


OLDEST TESTED.107 MOS. MATERIAL 
TESTING ON MINUTEMAN AND POLARIS. 


* NOTE: APROGRA 
MOTORS H 

'* CONTINUING MAT 


U PLAN DEFINING REQUIR 
AS BEEN PREPARED AND P 

ERIAL TESTING & ANALYT 


EMENTS FOR A 10 YEAR SHELFLIFE FOB ALL 
RESENTED TO NASA/SPO. 

ICAL PROGRAMS. 



Figure 71(b) - 1977 Status. 



MOTOR SHELFUFE SUMMARY 



MOTOR 


SHELFUFE (YRS) 


BASIS FOR PRESENT SHELFLIFE 


ACTIVE WORK 


PRESENT 


TARGET 


•ALGOL I IIA 


5 


10 


OLDEST FLOWN-46 MOS. MATERIAL AND 
BONDLINE TESTING/ANALYSIS.*, " 


SPECIMEN TESTING OF APPROX. 
8 YR OLD MOTOR PROPELLANT/ 
BOND SYSTEM PLANNED 


•aSTOR IIA 


9 


10 


OLDEST FLOWN-82 MOS. MATERIAL AND 
BONOLINE TESTING/ANALYSIS* AND 
STATIC TEST OF 9.8 YR OLD MOTOR 


INVESTIGATING METHODS TO 
EXTEND SHELF LIFE TO 10 YRS 


•ANTARES IIA 


9 


10 


OLDEST FIRED-126 MOS. MATERIAL 
AND BONDLINE TESTING/ANALYSIS 


NONE 


•ALTAIR IlIA 


6 


10 


OLDEST FIRED-56 MOS. MATERIAL AND 
BONDLINE TESTING/ANALYSIS.* 


NONE 


•ANTARES I IIA 


5 


10 


SUFFICIENT PLIMS MADE DURING DEVELOPMENT PHASE TO TEST 
ON AN ANNUAL BASIS FOR 10 YEARS. ONE MOTOR PLANNED TO BE 
SET-ASIDE DURING PRODUCTION FOR SHELF-LIFE PURPOSES."' 


« CONTINUING MATERIAL TESTING AND ANALYTICAL PROGRAMS. 

•• PROPELLANT AND BOND LINE TESTING COMPLETED TO 7 YEARS. 

«•• liy (.UNIIIALl. VLKlllCAIlUN IN I'HOCLSS. ILSl ING 10 1 YLAII UM-LLlt 



I 



Figure 71(c).- I98O Status. 






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194 



Castor I I (Figure 73) •- Presently this motor is qualified for a 9-year 
shelf life. However during the test program conducted to establish this 
shelf life, an increase in propel lant modulus was observed. This resulted in 
an apparent increase in the predicted thermal stress of the case/ insulat ion/ 
propel lant bond line in the head end and case center areas. This increase 
indicated a marginal condition for certain storage and flight temperature 
env i ronments . 

An ultrasonic inspection was initiated as part of the inspection criteria for 
motors in excess of two years old. Because of this condition additional inves- 
tigation of the propel lant mechanical and physical properties, both by labora- 
tory and the full scale static firing of a six year old motor was completed. 
Actual flight tests have been observed on an 82-month old motor. 

Altair IMA (FW-4$/TEM-640) .- The shelf life for the FW-4S motor is 
six years. This motor was replaced by the TEM-640 motor. The TEM-S^tO motor 
was procured from the Thiokol Elkton Division under NASl-11400. This contract 
required a shelf life program including real time composite and propel lant 
specimen testing on a semi-annual basis for 72 months. The case, nozzle, and 
igniter are identical to the FW-4S with the only difference being the liner 
and propel lant formulation. To date, the tests indicate superior physical 
properties when compared to the FW-4S and the 72-month shelf life study, com- 
pleted in 1979, was eas i ly obtainable Actual flight tests have been observed 
on 56-month old motor (figure 7^0 

BE-3- - Under contract NAS1-10000, Task S-033, a shelf life program 
included visua.l and X-ray inspections, a component shelf life review, and a 
full scale static firing of a motor in excess of 100 months old. No future 
use of BE-3 motor is planned. 

Antares I lA. - The shelf life for an Antares I lA is 9 years. Actual 
flight tests have been observed on a 126-month old motor. This motor has been 
replaced by the Antares IMA. (Figure 75-) 

Antares IMA (Figure 75) .- The shelf life for an Antares IMA is 5 years. 
This motor will be evaluated in Phase VII. 

It should be understood that the shelf life tests through Phase VI were a 
continuation of the Scout R&D effort initiated at the start of the program 
and that figures 71 through 75 will benefit Phases VII and VIM. ^ ' 

Table L itemizes the cost of shelf life program assigned to Phase VI. 

FOURTH-STAGE CAPACITIVE DISCHARGE IGNITION SYSTEM 

Significant system weight and size reductions can be realized when comparing 
a capacitive discharge ignition system to a wet-cell battery system. Programs 
such as Viking and Explorer have taken advantage of these factors by develop- 
ing and qualifying capacitive discharge ignition system flight hardware. 

(1)The charts of figure 71 thru 75 are official I979 documents and show S-192 
assigned to NOVA- 1 I . It was later reassigned to NOVA- 1 so that the last 
Phase Vi launch would be completed before S-192 aged any further. 



195 



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OF POOR qukU'fi 



TABLE L 



P.R. NO. 



PHASE VI 



ORDER NO. 



SOLID PROPULSION AND PYROTECHNIC SHELF LIFE 
AND AGING PROGRAM OBLIGATIONS 

ITEM J.O. NO. DESCRIPTION 



OBLIGATION 



First Stage (Algol I JC) 

NASI-I25OO-RI6 

Second Stage (Castor I |A) 
NASI-I25OO-RI6 

Third Stage (X-259) 

60.900.119 NAS1-10it83-3 
66.000.076 NAS1-10000-32-CA23-S 

NAS1-12500-R3^ 

Fourth Stage (X-258) 
66.000.076 NAS1-1OO00-32-CA23-S 
60.900.172 NAS1-1048l-it 
60.900.172 NAS1-10if8l-2 

Fourth Stage (FW-^S) 
60.900.122 NAS1-10000-14-CA13-S 
60.900.122 NASI-IOOOO-I4-CAI3-S 
6600.0931 NASI -1 0000-1 i|-CA13-S 

60.900.120 NAS1-10484-3 

Fifth Stage 

60.900.054 NASI -6935-43 

66.000.282 NAS1-10000-39-CA33-S 



222 E6OOOR Initiator Shelf Life Tests $ 905.00 
198 E7002R Initiator Shelf Life Tests 905.00 



672 
387 



672 

004 



E6OOIS 
E6OOOR 



E6OOIS 
E6002U 



326 E6OOOS 
315 E6185S 
314 E6188S 



346 E600OS 



X-259 Motor Shlf .Lf .Stdy. 7,000.00 
X-259 Motor Component Tsts. 40,979.00 
X-259 Motor Shlf .Lf. Stdy. 3,457.00 



Mtr.&lgn.Shlf .Lf .Ext. 40,979.00 
Tech.Spt.,Mtr.Shlf .Lf .Ext. 1 ,648.00 
Hydrotest X-258 Mtr.Chmb. 7,000.00 



FW4S Shelf Life Test 31,082.00 

DITTO 31,173.00 

DITTO 31,173.00 

Provide Motor Case Samples 1,200.00 



Motor Shlf .Lf. Study 
DITTO 

PHASE VI TOTAL 



15,602.00 
47.900.0 

$261 ,003.00 



Scout initiated a program to study, develop a preliminary design, and demonstrate 
the use of a capacitive discharge ignition system for use on the Scout vehicle. 
This system design was considered as a replacement for the Fourth-Stage Module 
System. The primary goal of this effort was to define a miniaturized system 
that could be contained in a single unit and would equal or exceed the existing 
system reliability. This was to be accomplished through the use of solid state 
electronics and by component selection that would allow the packaging of all 
existing redundant functions such as power, timing, safing and switching to be 
integrated into the existing Gulton timer (or equivalent size) envelope. It 
was anticipated that a 2-pound weight saving, equal to the present fourth-stage 
module ignition battery weight would be realized. 

This program consisted of the study, design selection and design breadboard i ng, 
and demonstration testing of a capacitive discharge ignition system. In support 
of the system study a test program was conducted to determine and evaluate the 
Scout SBASI pyrotechnic device firing energy requirements. The following 
presents a listing of the major activities associated with this program. 



199 

A. Initiate test plans and breadboard designs. 

B. Perform liaison with users and designers of capacitive discharge 
systems and coordinate with missile range safety offices. 

C. Conduct SBASI Energy Tests. 

D. Develop design concepts and conduct component surveys. 

E. Perform design trade studies and select concept. 

F. Complete design, breadboard the system, and conduct evaluation tests, 

G. Complete trade study analysis which includes assessments of relia- 
bility, weight and cost. 

H. Perform design review, finalize design and prepare final report. 

The program was completed successfully. 

SPARES PROCUREMENT 

The procurement of spares for the Scout Program comprise a major part of the 
Scout Spares Program. Quantities and costs are negotiated with the prime 
contractor. Upon completion of the negotiations the Government authorizes 
the prime contractor to procure the quantities of Scout hardware and GSE, as 
negotiated, for additions to the Scout spares program. The prime contractor 
either prepares purchase orders to all required vendors or initiates the 
fabrication process for all the Vought-manufactured items. 

The Spares Program in effect during Phase VI was initiated in I962. The 
contract history for the Scout Logistics and Spares Program is documented 
below. 

January 17, 1962 - First Logistics Spares Program Meeting. 
June 14, 1962 - First Spares Contract, NAS1-1970 (parts only). 
September 9, 1962 - Second Spares Contract, NAS1-2165 (management plus 

provisions for spares procurement and repair). 
September 30, I962 - Third Spares Contract, NASl-3420 (management plus 

provisions for spares procurement and repair). 
July 1, 1965 - Fourth Spares Contract, NAS1-4664, Task K (management plus 

provisions for spares procurement and repair). 
May 31, 1966 - Inclusion of Propulsion Motor Spares in Scout Logistics 

Spares Program. 
November 1, I966 - Fifth Spares Contract, NASl-6020, Task L (a continuation 

of NASI -ksek) . 

December 19, 1968 - Sixth Spares Contract, NAS1-7256, Task L (management) 

and Task M (materials). 
November 1, I97O - Seventh Spares Contract, NASl-10000, Task L (management) 

and Task M (materials). 
November 1, 19/3 - Eighth Spares Contract, NAS1-12500, Task L (management) 

and Task M (mater ia Is) .(' ^ 



' 'With the initiation of contract NASl-12500, the spares repair previously 
in Task L was transferred to Task M. 



200 



OF POOS 



Spares were contracted by "types of spares" with the following designations: 

Ml Pacl<ing and Crating Spares 

M2 Rewori< Spares 0) 

M3 Retest Spares 

HkA New Purchase of Spares 

M4b New Purchase of Consumable Spares 

M5 Advanced Purchase of Control Spares 

M6 GSE Spares Purchase 

M7 GSE Spares Repair 

The Scout Spares and Logistics Program and its operational procedures are 
contractually documented as LTV report number 3-30000/4R-87-F. Upon receipt 
of contractual authorization, the prime contractor (LTV) issues purchase 
orders to the required vendors and initiates the paperworl< for in-house 
fabrication, if required. The contracts called for inspection and flight- 
acceptance tests as required on the vendor-delivered spares as well as the 
LTV-manufactured spares. The spares were stored in the Scout "Stores Area" 
at LTV-Dallas, as well as at the Scout launch sites. When spares are 
assigned to the spares shelves they are noted on the distribution list as 
required and approved by NASA. This included keeping a perpetual inventory 
file on the spares received or shipped. 



The Spares Program was contracted to include the following requirements: 
A. Organizations 

(1) Logistics Organization - 

The Scout Logistics Program is outlined in figure 76. 



SCOUT PROGRAM 
MANAGEMENT 



MANAGER 
LOGISTICS 



NASA/LRC SCOUT PROJECT OFFICE 
MANAGEMENT 



CHIEF 

TEST OPERATIONS 

AND 

LOGISTICS 



HEAD OF OPERATIONS 



HEAD OF FIELD OPERATIONS 
AND 
LOGISTICS 



LOGISTICS SPARES 
SUPERVISOR 



SCOUT PROJECT OFFICE 
LOGISTICS COORDINATOR 



LTV/MSD-T DALLAS 

LOGISTICS 

COORD I NATOR 



WALLOPS ISLAND 

LOGISTICS 

COORDINATOR 

(OLC) 



WESTERN TEST RANGE 

LOGISTICS 

COORDINATOR 

(OLC) 



Figure 76.- Scout Logistics Organization Chart. 



^^^Designated as part of "L" prior to contract NAS1-12500. 



201 

B. Management Operations 

(1) Operate in accordance with an approved standard operating 
procedure. 

(2) Maintain ground support equipment and flight-ready spares on 
si te. 

(3) Maintain ready reserve in Dallas. 

(4) Complete quarterly accountability and status reporting. 

(5) Shelf life program. 

(6) Return failed parts: 

(a) Analysis. 

(b) Repair or replace. 

(c) Usage rate - reliability. 

(7) Recommend provisioning changes. 

(a) Operation needs. 

(b) Design changes. 

(8) Maintain control of on-site Government- furn ished equipment 
range stock. 

C. Accountability and Status 

Status information is disseminated to all program segments by the 
Quarterly Replenishment Requirements Report (Q.RRR) . 

(1) Spares listed as follows: 

(a) Vehicle Spares 

(b) GSE Spares 

(c) Pyrotechnic I terns 

(d) Shelf Life Index 

(e) Parts Listing for San Marco Range 

(2) Authorized Operating Level. 

(3) Inventory Status WTR-W l-Dal las-San Marco-MRB-Vendor . 
{k) Usage Previous Month - Usage Total. 

(5) Shelf Life Time and Retest Requirements. 

(6) Special Requirements: 

(a) Flight Acceptance Test Required. 

(b) Logbook Required. 

(c) Vendor Data Required. 

(d) Passivation Required. 

(e) Malfunction Reports. 

(7) Replacement Requirements. 

(8) Effectivity Limitations. 

D. Logistics Flow Pattern 

In the interest of control and accountability, the Scout spares 
flow plan routes all items through the Dal las Spares Stores thus avoid 
any direct shipments between a vendor and a field site. 



"a 



202 



E. Material Review Board 



When the total extent of a malfunction cannot be determined in the 
field, the item is returned to Dallas on MRA for further test or from Dallas 
to the vendor for test to determine the exact cause of the malfunction. 
After receipt and inspection at Dallas, the malfunctioned item is forwarded 
to the Material Review Board for further disposition. Review Board action 
ascertains one of the following: 

(1) Salvage and repurchase. 

(2) Repair or replace by Contractor. 

(3) Repair or replace by Vendor. 

F. Quarterly Replenishment Requirements Report (Q.RRR) Distribution List 



(1) Distribution by NASA-Langley Research Center 



(a 
(b 



(2) LTV Distribution 



(a 
(b 
(c 
(d 
(e 
(f 

(g 

(h 
(i 
(j 
(k 



Procurement - Contracts 
Scout Project Office 



NAVPLANTREPO (Dallas) 

NASA REMO (Dallas) 

6595th Space Test Group, Attn: VWZC 

NASA/Washington Headquarters 

Logistics Supervisor (Dallas) 

Off-site Logistics Coordinator (WTR) 

Off-site Logistics Coordinator (WFC) 

MRB (Dallas) 

Quality (Dallas) 

Chief Project Engineer (Dallas) 

San Marco Project Engineer (Dallas) 



is as shown: 

(1 copy) 

2 copies) 

2 copies) 

1 copy) 

1 copy) 

1 copy) 
5 copies) 

2 copies) 
2 copies) 
1 copy) 
1 copy) 
1 copy) 
1 copy) 



SYSTEMS MANAGEMENT PROCUREMENT 



The titled "Systems Management Contract" included much more than the title 
implies. The contract also included multiple types of contractual environ- 
ments covering different sections; one with fixed price incentive award (FPIA), 
a second with cost reimbursable tasks (CPFF) , and also a section for firm 
fixed price procurements (FFP) . The complex contract was simplified by 
designating the requirements with alphabets as follows: 



Task A - Program Management 

Task B - Payload Coordination 

Task C - Preflight Planning 

Task D - Data Reduction and Analysis 

Task E - Systems Engineering 

Task F - Reliability Program 

Task G - Standardization and Configuration Control 

Task H - Vehicle Processing 

Task J - San Marco Support 

Task K - Certification Training 



203 

''Task L - Logistics Support Management 

Task M - Spares Hardware 

Task N - Field Services and Launch Support 

Task P - NASA Langley Support Program 
^^^Task R - Special Requirements 
^^''Task S - Program Support 

Task T - Hardware Support 

Task V - Tooling £. GSE Maintenance 

Task W - Failure Investigations (if required) 
5) Task Y ' 

^5^Task Z 

Performance Incentive(^) 

Relocation of Off-site Personnel (^) 

ts'prisenterr'taMe u'""-'"'i."l'' '" ^ '^°"^ ^^'^^^'"^ Management Contract 
Tabfr?., ^ ? -,1 """"3 ^^'^ contract NAS1-10000 as an example 

Ihe serv ces for'lLh : T''^" '" ^°"'''^^' NASl-10000. Table LI itemizes 
the services for each task presenting the quantities and time periods of 
services on the contract. Table Lll deta i 1 s Tasks B C D H InH m f 

tssnrZ'Z Z ""^.^^^"^'ty performed on contract NASl-10000 (to al 11) 

Us ng the same designations it can be noted that three pref light p lanninqs 

Wh^^e'b^th'c^ntra" ^''^Z "^''-^''^ ^"' '''''^'^ ^ contract^N^SI-lSSio' 
Where both contracts are designated, the services were performed twice 

sJu^diriFsrid:""^^" '''"-' -'''''' -- ^--"^ -' "'- ^-^'"I'tv 

The numbers in table LI are the quantities originally contracted The 

numbers in table Lll are the actua 1 quant i t ies used . Any d if fer;ncls are 
negotiated at the completion of the contract. a-rrerences are 

The contractor completed each of these tasks as follows. 



Task A 



The prime contractor furnished, on a sustaining basis, program 
management for directing, coordinating and maintaining cognizance 
of all Scout contractual program activities. This task supplied 
management for all other tasks including all subcontracts. 



(^^Detailed in Chapter 6 page 232. 
I^JCost Reimbursable (CPFF) portion. 
l^V '™ '^'^^^ Price (FFP) portion. 

^Every^successful launch earned an award. Financially this is included 



III I obK w 



^^^'^'^HH^fK^^'''M-^"'^-^ ""^ "°^ contracted for initially, they could be 
(6)r- ^T "^^Jl^ '?^t.on to order vehicle hardware (Y) oP motors (Z) 
^bJFinancially this is included in Task (N) . 
(k) and (6) are not assigned alphabets contractually. 



TASK 



\\\\ 



204 
TABLE LI (a) - SUMMARY OF SERVICES, NASI -10000 



Management, 3"Year 

SPAC Reporting Dai ly 
3-Year Payload Coordination 

15 - PreUminary Trajectories (2-5) 

10 - Feasibility Trajectory Studies 
5 - Thermal Calculations 
5 - Dynamic and Vibrational Analyses 

15 - Payload Interface Drawings (^-N) 

15 - Payload Interface Drawings G.S.E. (^-N) 

13 - Heat Shield Designs (3-N) 

10 - Umbilical Designs 
50 - Users Manual Pages (new) 
75 - Users Manuals 

3 - SSTP Guide per Test Section 
Pref 1 ight Planning 

15 - Pref light Planning Reports (A-N) 

11 - Instrument Calibration Summary Reports 

12 - Pref 1 ight Review Presentations 
Final Fl ight Reports 

16 - Final Flight Reports (1-5)(A-RY) 
3-Year Systems Engineering 
3-Year Reliabil ity 

Malfunction Reports 
G 3-Year Standardization and Configuration Control 

1 - Family Tree Drawing List (Appendix C.) 
Drawings 

H Processing: 0„-179C(N), ]/2.-]kkR, I.-I8OC, 2.-181C, 3.-l82C(N), 
'».-l83C, 5. -184c, 6.-170CR(N), 7. -185c, 8.-I8IR, 9.-I86C, 
10. -187c, 11. -188c, 12.-190C(N), 1/2. -191c, 0.-189C. 

J (^) Tasks for San Marco (up to maximum 7^9 K) 

K 2 Training Sessions 

L 3-Years Logistics Support 
Spares Report 

m(3) Spares (up to maximum 500 K) 

N 3-Years Launch Field Services 
1-each OPS Plan 
Countdown Manual 

P 3"Years Lanyley Field Services 

2 - Film Progress Reports 
R Specials -R&D 

S Program Support - As Required 

T Additional Required Hardware 

V 3"Years Tooling Maintenance 

W Single Point of Failure Investigation (Appendix B.) 



(lj Mod 26 adds Production Support. 

(2) Mod 27 adds 252 K, Mod. 35 adds 239 K. 

(3) Mod 23 add., 250 K. 



TASK 



205 
TABLE Ll(b) - SUMMARY OF SERVICES, NASl-1 ZSOO"*" 



A Management, 3 Years 

B 3-Year Pay load Coordination 

6 - Preliminary Trajectories 

2 - Feasibility Studies 

5 - Environmental Studies 

9 - Pref light Brochures 

8 - Payload Interface Drawings 

8 - Payload Interface Drawings G.S.E. 

9 - Heat Shield Designs 

3 - Umbi 1 ical Des igns 

5 - Mission Analysis and Orbital Studies 
75 - Users Manuals 

3 - SSTP Guide per Test Section 
C Pref 1 ight Planning 

10 - Pref 1 ight Planning Documentation Task 

9 - Pref light Review Presentations 
D Final Fl ight Reports 

9 - Final Fl ight Reports 
E" 3-Year Systems Engineering 
F-V 3- Year Reliability 

Malfunction Reports 
G 3-Year Standardization and Configuration Control 
H Processing: 0.-188, 0,-186, 1.-189, 2.-193, 3.-192, 4.-194, 5.-195, 

6.-196, 7.-197, 8.-198, 9.-199, 10.-179, 1/2.-200, 1/2-191 
J Tasks for San Marco (up to maximum 1307K costs) 
K 3-Year Certification Training 
L 3-Years Logistics Support 

Spares Report 
M Spares (up to maximum II58K costs) 
N 3-Years Launch Field Services 
P 3-Years Langley Field Services 
R Specials -R&D 
S Program Support - As Required 
T 5-Months of Vehicle Production Support 
y 3-Years GSE and Tooling Maintenance 
W Failure Investigations 



-MOd iKj aaas froauctioti Support for Algol 11! Mote 
+Does not include final MOD for services not used, 



206 



TABLE LI I (a) - DETAILS OF SERVICES, NASI -10000 



TASK 




(B) 


(c) 


(D) • 


(H) 


(N) 


Contract 




(1) &(9) F.S.) 


(18) 


(li.) 

Final 


(14) 




Vehicle 




Prel iminary 


Pref 1 ight 


Flight 




Launch 


Number 


Pay load 


Trajectories 


Planning 


Reports 


Process i nq 


Number 


17^0 


OFO 


7256 


7256 


1 


7256 


70 


175C 


SAS-A 


7256 


7256-17 


2 


7256 


71 


173C 


San Marco C 


7256 


5 


3 


7256-R3 


72 


l^itCR 


PAET-A 


1 


3 


k 


P-1--R-2-10 


73 


177C 


SOLRAD-D 


7256 & F.S. 


7256-18 


5 


7256 


74 


180C 


CAS-A 


7256 


7 


6 


P-2 


75 


166C 


GRP-A 


7256 & FS 


k 


7 


7256-R8 


76 


163CR 


SSS-A 


7256 


6 


8 


7256-R9 


77 


183C 


UK-4 


7256 


11 


9 


P-6 


78 


l8i4C 


MTS-A 


2-5 


13 


10 


P-7 


79 


182C 


NA-15(i) 
CAS-B^^ 


X 


9-1^ 


11 


P-5 


80 


181C 


X 


X 


X 


P-k 


X 


170CR 


SAS-B 


k 


12 


12 


7256 S-9 


81 


185C 


ESRO-IV 


3-6&FS 


8-^6 


13 


P-8 


82 


181CR 


AEROS-A 


7256 


1^ 


P-9 R30 


83 


178c 


NA-16 


X 


1-10 




7256-R 


8k 


179CC 


NA-18 


7256 


2 




P-3 




187 


UK-5 


9 & FS 






P-10 


90 


186c 


AEROS-B 








P-12 


88 


195 


TIP-2 


(i) 11 & FS 








92 


188 


UK-X4 


8 6 FS 






P-ll 


86 


189 


ANS-A 


7-10 & FS 






P-15^v 


89 


190 


SM-C2 








P-I3 


85 


191 


NPE-A 


FS 






PlZ+-,v 


87 


196 


DAD 


FS 








93 


\3ii 


SAS-C 










91 



"Partial Processing. 

(^)CAS-B was canceled and AEROS-A assigned to Scout S-I8I. 



207 



ORlGir^AL PAQE gS 
OF POOR QUALITY 



TASK 



TABLE LI 1(b) - NASI -12500 DETAILS 
(B) (C) (D) 



(H) 



(N) 



Vehicle 




Prel iminary 


Pref 1 ight 


Final Fl ight 




Launch 


Number 


Pay load 
NA-16 


Trajectories 


Planning 
10000^^^ 


Reports 


Processing 
7256 


Number 


178c 


1 


Sk 11 


190 


SM-C2 




1 


2 


10000 


85 


188 


UK-X4 


10000 


2 


3 


10000 


86 


191 


NPE-A 


1 


3 


4 


Vrl 


87 


186c 


AEROS-B 


2 


5 


5 


10000 


88 


189 


ANS-A 


10000 


6 


6 


2 


89 


187 


UK-5 


10000 


7 




10000 


90 


19^ 


SAS-C 


e:s:(^) 


Rill 


Rill 


5 


91 


195 
196 


NA-17 
DAD-A 


8 
R12VR125 


R157 
7 


6 
7 


92 

93 


179C 


AF-STP 


6 & E.S.(if) 


R165 


R165 


10000, 11 


(2) sk 


193 


GP-A 


3 & M.A.S. 


9 


8 


3 


95 


197 


TIP-MI 




R123/R126 


9 


8 


96 


198 


UK-6 


E.S.(4) 






9 




199 


NA- Backup 




10 




10 




200 


TRANSAT 


E.S.(4) 






12(1) 




201 


HCMM 


5 










192 


NA- Standby 

AO-7 

HAWKEYE-2 


M.A.S, 

F.S.(5) 

F.S.(5) 


k 




k 





10000 



(l)Partial 

\2) Task R 
(3) 10000 (NASI -10000) 
(5) F.S. Feasibility Study 
(i+) E.S. Environmental Study 



208 OF POOR QUALJTY 

Scout Program reviews were scheduled semiannually. The Scout review scheduled 
for April 5, 1973 is presented in appendix D. Note the review is complete, 
presenting the up-to-date data and status of the Scout program. It presents 
the contractor's organization, the current progress, the results of investiga- 
tions and studies, the beginning of production for the next phase, new develop- 
ments, and advanced planning. Program reviews are attended by NASA, DOD, and 
Vought Corporation with both NASA and Vought making presentations to top manage- 
ment of both organizations. Management reviews are also conducted by NASA with 
Vought Corporation. 

Contract and financial reviews are held with NASA Langley making the presenta- 
tion to NASA Headquarters. 

The 1975 NASA Scout Project Office Management Team is shown in figure 77. The 
Vought 1975 Management Organization is detailed in figure 78. By comparing 
figure 78 with Appendix D (Figure D-7) the changes in personnel in a two-year 
time period can be analyzed. The total manpower from 1964 through 1975 at the 
prime contractor's plant is shown in figure 79. The major contractor's man- 
power on the Scout program are illustrated in figure 80. 

On June 15, 1973, the results of a manpower study was disclosed in a memorandum 
for record. This study made by the NASA Scout Project Office was initiated 
January 1973. The study was made to determine the number of contractor personnel 
required to process and launch a Scout vehicle. Excerpts from this study are 
presented. The basic concepts or guidelines for the study were: 

"1. Retain the minimum field personnel required to efficiently perform 
routine field site tasks - periodic maintenance, clerical work, etc. 

"2. Utilize Dallas processing personnel in the launch crew and field 
personnel in Dallas processing. 

"3. Engineering personnel for launch crew to be derived from tasks A and 
E of the management contract. 

"k. Hold processing schedule to as near 30 days as possible using approxi- 
mately 37 people in the launch crew. 

"5- Navy missions have overall priority. 

"6. At the beginning of the next contract period, four vehicles will be 
complete through Dallas processing and ready to ship, and one vehicle will be 
complete through processing up to, but not including, bench tests. 

"7- During the next contract period, five vehicles will be completely 
processed in Dallas; one vehicle will be processed through bench tests, 
system tests, and prepared for shipment; and one vehicle will be processed 
through bench tests. 

"8. Tasks E and H of the next management contract are to provide for 
approximately ^k equivalent men each. 



OR^GlN/^t PAGE B 
OF POOR QUAUTT 



209 



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OF POOR 01 



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FINANC 
AOMIN 
E. A. 

PROGRA 
AOMIN 

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PROJECT ENGINE 
PROPULSION 

C F MACHAL4 


PROJECT ENGINE 
MISSION 
ANALYSIS 

GW KREITER 




PROJECT ENGINE 

6.S.E. 
R. O. SURRAT1 




PROJECT ENGINEI 

PAVLOAO 

COORDINATION 

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FLUID CONTROL * 
THERMAL ENVIRON. 

L.B.JOHNSON 


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PROJECT ENGINE 
ELECTRICAL* 
ELECTRONICS 

E.WALTERS 

1 


K 




PROJECT ENGINE 
MECHANICAL 

R FIELDER 


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211 



ORIGINAL PAGE IS 
OF POOR QUALITY 



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OF POOR QUALITY 



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214 



"9. Base scheduling upon ten launches, two of which are to be from the 
San Marco Range. 

"10. Assume no support of San Marco Range." 

As an initial estimate, the minimum field crew per guideline was determined 
to consist of 9 persons: 

Site Supervisor (Electrical Engineer) 

Secretary 

Engineering Supervisor (Mechanical Engineer) 

Air Frame/Fluids Mechanic 

Mechanical GSE/Fluids Mechanic 

Electrical GSE Technician 

Electrical Vehicle/GSE Technician 

Gu i dance/ 1 nst rumen tat ion Techn ic ian 

Quality Control Inspector 

This number was considered a base line for the study, and was assumed to be 
the permanent staff at each field site. 

The Dallas effort was outlined and scheduled using inputs from the NASA/REMO 
and contractor personnel. The manufacturing personnel required for vehicle 
processing is presented in Table LI II. 

The next undertaking was to develop a specific manpower list which would 
include all personnel at the field sites and those in tasks E and H at Dallas 
plus one from Task A (the Assistant Administrator) and one from Task L (the 
field logistics coordinator/expediter). The final list is presented in 
Table LIV. It was selected from all the others submitted because it demonstrated 
more efficient utilization of available personnel. 

TABLE Llll - MANUFACTURING PERSONNEL REQUIRED FOR VEHICLE PROCESSING 



WEEK 


WORK PERFORMED 


PERSONNEL REQ'D 


1 


Str. Mods. L/B 
Str. Mods. L/D 


1 Mech. 
1 Mech. 


2 


Str. Mods. L/B 
Paint L/B 
Str. Mods. L/D 


1 Mech. (1/2) 
Paint Shop 
1 Mech. 


3 


Paint L/B 
Elect. Mods. L/B 

Str. Mods. L/D 


Paint Shop 

1 Veh. Elec. & 

Dept. 250 
1 Mech. 


k 


Component Removal and Installation L/B 

Str. Mods. L/D 
Pnint L/D 
Str. Mods. U/D 


1 Mech. (1/2) 
1 Elec. (1/2) 
1 Mech. 
Paint Shop 
1 Mech. 



215 



WEEK 



10 



TABLE LI I I Continued - 
MANUFACTURING PERSONNEL REQUIRED FOR VEHICLE 
WORK PERFORMED 



PROCESSING 



Str. Mods. U/C 
Elect. Mods. L/D 
Str. Mods. U/D 
Elect. Mods. U/D 



Str. Mods. U/B 
Str. Mods. U/C 
Component Removal and Installation L/D 

Component Removal and Installation U/D 



Str. Mods. B/A 



Str. Mods. U/B 

Elect. Mods. U/C 

Component Removal and Installation L/D 



Str. Mods. B/A 



Elect. Mods. U/B 

Str. Mods. L/C 

Component Removal and Installation U/C 

Paint B/A 



Elect. Mods. T/M 
Elect. Mods. B/A 
Component Removal and Installation U/B 

Str. Mods. L/C 

Paint L/C 

Component Removal and Installation U/C 

Join and C/0 U/D - L/D 



Elect. Mods. T/M 
Elect. Mods. B/A 
Component Removal and Installation B/A 

Component Removal a"H inct-ai ia«- ;^r. h/d 

Elect. Mods. L/C 

Component Removal and Installation L/C 

Paint U/C 

Join and C/0 U/D - L/D 



PERSONNEL REO'D 



Mech. /Fluid 
Elec./Dept. 250 
Mech, (1/2) 
Elec./Dept. 250 



Mech. /Fluid 

Mech. /Fluid 

Mech. 

Elec. 

Mech. 

Elec. 



Mech. /Fluid 
Mech. 

Mech. /Fluid 
Elec./Dept. 250 
Mech. 



Mech. /Fluid) 
Mech. )Al/^; 

Elect. /Dept. 250 
Mech. 
Mech. 
Elec. 
Paint Shop 



Elec./Dept. 250 
Elec./Dept. 250 
Mech. /Fluid 
Elec. 

Mech. (1/2) 
Paint Shop 
Mech. /Fluid 
Elec. 
Mech . 
Elec. (1/5) 



Elec./Dept. 250 

pt. 250 (1/5) 

Mech. /Flu id 

Elec. 

nech ./F I u id 



Elec. 
Elec. 
pt. 250 
Mech. ) 
Elect.)' 

Paint Shop 

2 Mech. 

1 Elec. (1/5) 



jXl/2) 
:>(1/2) 



216 



OF POOR QUALHY 



WEEK 



TABLE LI I I Concluded - 
MANUFACTURING PERSONNEL REQUIRED FOR VEHICLE PROCESSING 
WORK PERFORMED PERSONNEL REO'D 




Component Removal and Installation B/A 
Section C/0 B/A 

Paint U/B 

Component Removal and Installation L/C 

Section C/0 U/C 

Section C/0 U-L/D 



tion B/A 


1 Mech. /Fluid 




1 Elec. 




1 Mech. /Fluid 




1 Mech. 




1 Elec. 




Paint Shop 


:ion L/C 


1 Mech. 




1 Elec. 




1 Mech. /Fluid) 

1 Elec. y(Ul) 




2 Mech, 




1 Elec. (1/5) 



Base "A" 
Lower "B 
Upper "B 
Lower "C 
Upper "C 
Lower "D 
Upper "D 
Te 1 erne try 



Task B 



The contractor provided continuous liaison and mission worl<ing group 
representation on all matters pertaining to payload integration for 
both domestic and international payloads for all requirements. For 
all missions, the contractor verified internal contractor intergroup 
technical capability for each mission, and maintained cognizance and 
schedules of all inputs into a final trajectory calculation consisting 
of flight motors, flight weights, pitch program, aerodynamics, and 
spin motor utilization. 

In support of vehicle processing, the contractor provided internal 
coordination to assure schedule compatibility of payload peculiar production 
items, such as heat shield production and modifications, heat-shield ejection 
tests, heat-shield fit checks, separation system tests, transition sections 
and separation systems, RFI tests, umbilical plugs and cables, and special 
payload agency-procured studies and items pertinent to the Scout vehicle. 

The contractor within a category titled General Coordination made 
preliminary design layouts of payload interfaces, and verified their compati- 
bility with the Scout vehicle. These layouts included the following: 

Heat Shield 
Separation Systems 
Separation System Wiring 
Transition Sections 
Fourth-Stage Rocket Motor 



217 



ORIGINAL PAGS Va 
OF POOR QUALITY 



TABLE LIV - MANPOWER LIST (PLAN "B") 
SLOT NO. SKILL DESCRIPTinN 



LOCATION 



1 Field Site Supervisor 

2 Field Site Supervisor ^' 

3 Engineering Supervisor ^^^ 
'* Engineering Supervisor *{^ 

5 Assistant Administrator 

6 Field Logistics Coordinator/Expediter haI" 
/ Secretary '^"'- 
o Secretary "' 

9 M. GSE/Fluids Technician (Leadman) JJ!^ 

M. GSE/Fluids Technician (Leadman) 7.!.. 

1 Airframe/Fluids Technician J^, 
12 Airframe/Fluids Technician J^' 

3 Airframe/Fluids Technician Zlv 

^ Airframe/M. GSE/Spin Technician ^td 

5 Airframe/M. GSE Technician (Leadman) „!? 

6 Airframe/M. GSE/Spin Technician Std 
1/ Airframe Mechanic ^^^ 

18 Airframe Mechanic '^^^ 

19 Vehicle/E. GSE Technician ^^'- 

20 Vehicle/E. GSE Technician ,,' 

21 Vehicle/E. GSE Technician i^J? 

22 Vehicle/E. GSE Technician JJ^ 

23 Vehicle EL. Technician ^^^ 
2h Vehicle EL. Technician °J^[ 

25 Elect. GSE Technician ^,'- 

26 Elect. GSE Technician 7.1.. 

27 Guidance/T/M Technician 7/ 

28 Guidance/T/M Technician J^' 

29 Guidance Technician J^™ 

30 Guidance Technician JJ*" 

31 Instrumentation and T/M Technician nAl" 

32 Instrumentation and T/M Technician wCr 

33 RF/lnstrumentation/E. GSE Technician dai 
3^ RF/lnstrumentation/E. GSE Technician utd 

35 Vehicle/GSE Q.C. Insp. 7,\*^ 

36 Vehicle/GSE O.C insp. J^' 

37 Vehicle Mech. Q.C. Insp. JJ^ 

38 Vehicle Elect. Q.C. Insp. ^J,^ 

39 Mech. Veh./GSE Engineer (2) Z^, 
^0 H202/Fluids Engineer (2) ^J,"" 
1*1 Elect. Veh./GSE Engineer (2) nfii 
f*2 Guidance Engineer (2)-~-~^ "- 
"^3 Instr./R.F. Engineer (Z)''^'' ''"^-^ Conductor ^'^^ 
'^ Ignition/Destruct Engineer (2) haI" 
^5 Q.C. LDR/Supervisor Engineer (1) p^L 



218 

Fifth-Stage Rocket Motor (as required) 

Umb i 1 ical Systems 

Pay load Pertinent Launch Complex and/or Associated Ground Support 

Equipment (GSE) • 
Other Interfaces 
Other Interfaces Involved With Secondary Payloads and/or Special 

Separation Systems Furnished by Scout Users 

The contractor maintained cognizance of the Scout User's Manual ^^^ 
revisions and also a User's Manual distribution control program. The contractor 
performed all work necessary to maintain in a current and accurate status, all 
material contained in the User's Manual. The contractor provided and distrib- 
uted revised pages for all copies of the manual In existence. The contractor 
distributed additional copies of the User's Manual as directed by the NASA 
Scout Office. 

The contractor furnished three copies of the Scout separation system 
test planning guide to each Scout user with each test section provided. The 
contractor maintained the Scout separation system test planning guide in a 
current and accurate status. 

The contractor prepared a pref light brochure for each launch vehicle 
and issued this document thirty days prior to a scheduled launch. 

The contractor provided preliminary trajectory calculations with 
respect to performance capability, range safety, and tracking. 

The contractor completed mission analysis and orbital studies as 
specified by NASA. Figure 81 defines long-range mission scheduling. 

The contractor prepared and issued vehicle and GSE payload interface 
drawings. These drawings were approved by all members of the Mission Working 
Group and when submitted in final form they included identification of all 
pay load/veh icle and payload GSE interface technical requirements. 

The contractor completed all engineering necessary to define heat 
shield modifications required for each mission. Figure 82 shows heat-shield 
door locat ions . 

The contractor provided all engineering necessary to define payload 
umbilical cables for each mission. 

Tables LI and LI I list the contractual details of the services obtained 
in Task B. Figure 83 itemizes vehicle furnished services and materials for pay- 
load integration. 

Although the payload coordination contractor effort was contractually 
covered, the mission responsibility (as it relates to the launch vehicle) was 
outside the scope of the contracts. Since the area of general payload-to- 
vehicle integration and payload coordination involved a number of different 

(^^User's Manuals are provided for all payloads assigned to Scout vehicles. 

This Manual acquaints the user with the capabilities of the Scout vehicle and 

provides detailed design information to aid the engineer in integrating his 
spacecraft with the vehicle. 



iS4S»^ l^ 



ORIGINAL PAG 
OF POOR QUALITY 



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OF POOR 



01} 






"E" SECTION 
UMBILICAL DOOR 
I 
-<t- 



4TH STAGE IGNITION 
SQUIB ACCESS DOOR 
1 REQ. 




VENT(V) DOORS 
4 REQ. 



END LIMITS OF 
ALLOWABLE AREA FOR 
P/L UMBILICAL DOOR 

PAYLOAD ACCESS DOORS MAY BE ADDED AS REQUIRED 

Figure 82.- Scout Heat-shield Door Locations. 



1. PAYLOAD SEPARATION SYSTEM 

2. HEATSHIELD MODIFICATION (AS REQUIRED) 

3. SCOUT USER'S MANUAL AND DESIGN DATA 

4. PAYLOAD UMBILICAL CABLE 

5. LAUNCH COMPLEX WIRING 

6. MISSION PLANNING 

7. RANGE INTEGRATION 



Figure 83.- Scout Vehicle Furnished Services and Materials for Payload Integration. 



t^ 



ORlQ't^lAi: PAS 

OF POOR QUALITY 



221 



agencies, a submanagement organization was formed to coordinate these agencies 
and their activities. This organization has been called the Mission Working 
Group. The Scout Project Office, the Range, the Contractor, the Payload 
Agency and the Department of Defense had personnel assigned to the payload 
Mission Working Group which was organized as follows: 



Mission 
Working Group 




Payload 
Agency 



Range 



Lang ley 

Scout Project 

Office 



Ling Temco Vought I 
Dallas I 



SAMSO 

(DOD Missions 

only) 



Specifically, this group is responsible for the direction of all documentation 
effort; the physical integration program; the operational integrat ional pro- 
gram; and IS, in general, charged with mission responsibility at the working 
level. The Scout payload coordination plan is outlined in table LV . 

Task C - The contractor performed the pref light planning tasks necessary to 

deliver a payload to a designated flight condition at, or after, the 
last stage burnout. Portions of the resulting documentation are 
revised, when necessary, to reflect final stage and spacecraft weights 
or motor assignments. Predicted motor performance data for each motor 
was reevaluated, reviewed, and updated using actual motor flight per- 
formance results. This was accomplished by using representative motor 
data from the maximum number of the most recent flights; not to exceed 
eight. The techniques used are described in LTV Report 23.420. 

The contractor determined the vehicle weight breakdown, center of 
gravity, three major moments of inertia as a function of consumable remaining 
weight and time histories. 

The contractor defined the actual final mission flight profile based 
upon the motor performance and the above-determined weights, and also defined 
the final vehicle pitch program for each spacecraft mission. 

The contractor prepared each final flight trajectory in the format 
of contractor routine LAOO76. 

For D.O.D. launches the contractor calculated optimum launch time, 
with the following Government-provided information: 



i-.iii- :.-..-" 1 



trrective time period, ana 
Orbital data for each spacecraft. 

The data consisted of the desired right ascension of the ascending node for 
a given day and its rate of change per day from that day. 



222 



TABLE LV - SCOUT PROJECT PAYLOAD COORDINATION PLAN 



Months 



■2k 



EVENTS 



1. 
2. 
3. 
k. 

5. 
6. 



Pay load assigned to Scout 

MWG formed 

Launch site selected 

Design data to pay load agency 

Payload design data to vehicle 

Establish documentation rqmts. 



■20 MWG Review 1 

1. Establish approx. launch date 

2. Determine performance and 
accuracy requirements 

3. Prelim, heat shield design 
k. Payload tracking coverage 

5. Define spin 1 imi ts 

6. Review range documentation Req 



-16 MWG Review 2 

1. Establish launch date 

2. Define boost trajectory 
constraint 

3. Define prelim, payload mission 
requi rements 



-13 1. Define final design of payload 
system and heat shield 
2. Define wiring required for pay 
load flyaway umbilical cable 



-1 1 MWG Review 3 

1. Sys. design integration compl . 

2. Submit range documentation 

3. Define heat shield eject, test 
requirements and date for test 

^4. Provide 3 D.O.F. trajectories 
to payload agency 



Payload configuration and mission 
defined to permit contractor to 
proceed with Range Safety Report 



Days 



■180 



-60 



-30 



-15 



-10 



EVENTS 



-9 



MWG Review k 

1. Final date for start of range 
safety study 

2. Definition of vehicle motor 
performance 

3. Spin motor req. final 

k. Review and establish firm 
launch data 

5. Heat shield ejection test at 
Dal las 

6. RFI check at Dal las 



Range Safety Study to WTR 



1. 
2. 



Payload arrives at launch site 

Final trajectory due at launch 

si te 

Configure launch complex for 

payload 



Pre-pad checks 

Payload and vehicle simulated 

f 1 ight and RFI checks 



1. Spin balance payload and veh, 
fourth stage together 

2. Physical measurements 



Final Preassembly checks 



1. Mate payload with vehicle at 
pad 

2. Vehicle, and payload RFI check 
at pad 



LAUNCH OPERATION 



223 



A Design Information Release (DIR) as outlined in letter SL-2365/JCP 
dated June 19, 1973, was issued for each launch This DIR included all the 
results of the Task C requirements as follows:^^^ 



Prefl 
Pref 1 
Prefl 
Prefl 
Prefl 
Prefl 
Prefl 
Prefl 



ght motor assignment and performance. 

ght weight description. 

ght sequence of events and guidance program. 

ght control settings and hydrogen peroxide requirements. 

ght performance profile. 

ght wind restriction. 

ght spin rate predictions. 

ght final trajectory, look angles, and stage impact points. 



Data system calibration 

The contractor provided a pref 1 ight review presentation at the NASA 
Langley Research Center office for each launch vehicle processing, all problems, 
motor history, prior launch-pertinent information and contractor's opinions 
were presented to a group of Government experts which resulted in the "0 K to 
Launch" decision. 

A typical prefl ight report is reproduced in Appendix E- 

Task D - The contractor completed all effort necessary to reduce, analyze, and 
report vehicle flight results for each mission. These results include 
motor burn, coast, orbital insertion, and analysis of any anomalies. 
Flight data trends or biases that could jeopardize "safety of flight" 
for vehicle or mission was reviewed by the contractor and reported 
to NASA. 

The contractor prepared and submitted the final flight results for each 
mission in a report entitled, "Final Flight Report" within sixty days of 
receiving the required data from NASA. The report was required to be prepared 
as was LTV Postf 1 ight Report number 3-3^1 00/ IR-8I . A typical flight report is 
reproduced in Appendix F. 

Task E - The contractor supplied the system engineering effort necessary to 
support all aspects of the activity associated with the following 
systems: 

Mechan ica] 

Control 

Gu i dance 

Electrical and Electronic 

Propulsion and Pyrotechnics 

Launch Complex and Ground Support Equipment 



^^'^^■^?"^oo^^°'' ^^^ required to submit to the Government a list of all new 
DIR's 30 days prior to each launch. 






224 



The engineering to support this effort consisted of the following: 

Initiation, review, and disposition of revisions to the Scout Standard 
Procedures, the Standard Scout Vehicle and G.S.E. configurations. 

Review and/or disposition of system and component deviations. 

Review of all discrepancies, making appropriate recommendations. 

Insure compliance with Scout technical standards at all sites includ- 
ing subvendors and storage facilities. 

Notification to the Government of any significant technical problems 
in an expeditious manner. 

Notification to the Government of any situation that could jeopardize 
flight performance. Notification to be made to insure receipt prior 
to the start of launch countdown. 

Notification to the Government of any action necessary on its part to 
permit the contractor to fulfill his contractual obligations. 

The contractor also reviewed the vehicle and ground support equipment 
environment, design, manufacturing and performance (including vendor component 
and subsystems), to find, analyze, and resolve problems, and implement changes 
resulting from the following items: 

Safety-of-f 1 ight Items. 

Capability of the contractor and subcontractors to process consistent with 
Scout Standard Operating Procedures. 

Engineering resolution of problems. 

Producib i 1 i ty changes. 

Government-approved, Contractor-requested changes. 

The contractor also provided liaison to quality control, manufacturing, 
materials, and launch activities to insure compatibility of all Scout systems. 

Task F - A Reliability Program was managed by the contractor which included the 
tasks necessary to support vehicle production, in-plant and field pro- 
cessing of vehicles, and Scout system product improvement in accordance 
with applicable revision of LTV reports 23-203 and H .Ihl . ^^' 

Task G - The contractor maintained a Standardization and Configuration Control 
system that provided for the receipt, evaluation, and recommendation 
of changes to the Scout Standard Operating Procedures, vehicle and 
GSE configurations. The objective of this standardization and configu- 
ration control system was to provide for the interchange and evalua- 
tion of technical data, experience, and knowledge existing at the 
various Scout operating sites (Wallops Island, Vandenberg AFB, San 
Marco, NASA/Langley Research Center Scout Project Office, and 
contractor's Dallas facility). The contractor operated the configu- 
ration control system in accordance with LTV report 3-1 5000/5R-240 
titled "Configuration Control Operating Procedures for the Scout 
System," and with LTV report 3-30000/4R-81 titled "Standard Operating 
Procedures Editorial Plan." 



(a)Detailed in Chapter 5- 



225 

These reports include the following requirements: 

"1. The contractor shall maintain storage and issuance control for Standard 
Operating Procedures manuals. Additional data accumulation and Quality Assur- 
ance packages at the Contractor's Dallas facility, Vandenberg AFB, and Wallops 
Island shall be reproduced locally by the user consistent with usage rates 
The contractor shall also provide revised pages to the Standard Operating Pro- 
cedures Manuals, as they are required due to changes as authorized under Stan- 
dardization and Configuration Control. 

"2. The contractor shall maintain and correct the system of drawings and 
specifications which defines all the latest vehicle and GSE configurations 
Within thirty days of their effectivity date, two microfilm and three prints 
of each contractor and subcontractor Engineering Order (E.O.), and each con- 
tractor specification shall be furnished to NASA Langley Research Center Scout 
Project Office. Drawings, Engineering Orders, and Specifications furnished 
under other Scout contracts shall have their identification included in all 
listings supplied under this contract. All active drawings shall have no more 
than four E.O.'s outstanding at any time. A production drawing shall be made 
for each vehicle modification drawing (Standard Configuration only) within 
thirty days of effectivity date of each modification drawing. The standard 
GSE configuration shall be identified by family tree drawing lists of Scout 
Standard System Test Equipment, Scout Launch Complex equipment, and trans- 
porters. The documentation shall be maintained or provided as follows: 

"(a) Scout Standard System Test (S3T) equipment drawings shall be 
maintained for Wl and VAFB. 

"(b) Standard Launch Complex (SLC) drawings for the launcher equip- 
ment shall be maintained for Wl and VAFB. Those drawings peculiar to vehicle 
processing (functional schematics, wire books and component location charts) 
shall be maintained on site. Reproducible drawings of this equipment shall 
be forwarded to the contractor and an index of available drawings maintained. 

"(c) Dynamic Spin Balance facility procedures and drawings shall be 
maintained at Vandenberg AFB. 

"(d) The portable and mobile GSE drawings shall be maintained and 
corrected. Reproduc ibles or originals of these drawings shall be integrated 
in the contractor's drawing system. 

"(e) The contractor shall maintain a family-tree drawing for the 
standard Scout vehicle incorporating all drawings down to the component instal- 
lation level for 3-, k- , and 5-stage vehicles. 

"(f) The contractor shall maintain a family-tree drawing for Scout 
Ground Support Equipment. 

"(g) The contractor shall provide the following indexes Lo NASA/ 
Langley Research Center Scout Project Office every ninety days except as noted; 

Alphabetical Drawing Index 

Numerical Drawing Index 

Numerical Specification Index 

Standard Operating Procedures Cross Reference Index (semiannually) 



226 



"3. The contractor shall provide a Standard Procedure Configuration 
Index for each vehicle prior to processing each vehicle through checkout. 
This index shall identify the Standard Procedures to be used by page and 
revision date and shall be used as the means of procedure planning documen- 
tation. This index shall be attached to the applicable vehicle logbook. 
A similar index for the field portion of the Standard Procedure shall be 
submitted to NASA/Langley Research Center Scout Project Office two weeks 
prior to the start of vehicle processing in the field." 

Task H - This task covers the task of vehicle processing. This covers the 
effort of getting the vehicle ready for launching which includes: 

Remove the vehicle from storage. 

Depreserve and examine all vehicle sections for completeness, 
condition and compliance to lobgook entries. 

Inspect and/or test major items and components as per QCPP-0-005C 
and correct any deficiencies revealed during such inspections or tests. 

Provide the effort necessary to implement changes resulting from: 
Safety-of-f 1 ight items, 

Revisions necessary to provide capability to process vehicles 
consistent with Standard Operating Procedures and Standardi- 
zation and Configuration Control, and 
Modification necessary to produc ib i 1 i ty . 

Pay load Umb i 1 ical . 

Vehicle Mods. 

Configure for Fl ight . 

Check Out. 

Engineering, manufacturing, and quality liaison representation in the 
Dallas processing and field checkout and launching of vehicles. 

Notification by the Government of each vehicle's launch site and 
expected payload assignment at least five months in advance of each vehicle's 
expected shipping date. 

'' ■'One heat-shield fit and ejection test of hardware designated by the 
contracting officer. This test shall be made using the free-fall method per 
SOP. A prototype or mockup payload, if required, shall be furnished as Gov- 
ernment Furnished Equipment on a time scale consistent with ejection test 
schedule. Upon completion of the ejection test, five copies, and one repro- 
ducible of individual summary report similar to LTV report 23.317 and one 
copy of the ejection test motion picture film shall be submitted to the NASA 
Langley Research Center Scout Project Office. 

Conduct and report on heat sh ie Id- to-pay load vehicle fit checks in 
accordance with Standard Operating Procedures. 

Processing for launch from the Standard Launch Complex (SLC) shall 
follow the Standard Operating Procedures defined in LTV report 3-1 5000/5R-240 , 
as revised. 

Upon assignment of the Government-furnished rocket motors to a 
vehicle, the contractor shall conduct an inspection, and shall prepare the 
motors for integration into the vehicle in accordance with Volume I 11 of the 
Standard Operating Procedures and the flow charts of Volume I of the Standard 
Operating Procedures. 



(3)Figures Sk, 85, and 86 reflect the Scout payload processing and tests 
completed for many of the Scout pay loads. 



227 






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OF POOR QUALITY 

of the pavload'Ld'v.'h?","'''rH-°" '"°'' '"' ^" responsible for integration 
of the payload and vehicle including spin balance at the launch site 

Prepare R-Day (launch date) schedules showing spacecraf t/ranqe inter- 
he'R^Z'sch^d'?- ^^^^"^-^-3 AFB the NASA/DOD Joint Office shal^; ove 
the R-Day schedues indicating compliance with Range Support Requirements 

The contractor defines support requirements, and prepares all appli- 
cable range documentation, preflight and 24-hour data reports and all other 
necessary documentation. The contractor assures that these documents are 
maintained in a current status. 

evaluation^^r""'^^'"'"/"'"'''''^'" '" 3'°""^ ^"^ '"^"^e safety analyses and 
evaluations of range safety restraints and informs the NASA and the 6595th 

r^nn^^^f I"' !!'"^ °^ ^"^ proposed changes that affect the NASA/DOD Scout 
range safety and range safety-related programs. This information is needed to 
iZch '■^^^^'■^"^euts for Range Safety approval ninety days before each 

Responsible for maintaining the necessary ground and range safety 

NA.A/WTP M- '"? c '''"^' '"^"^"'^ ^"'^ ^°'' '^^ '^^-'"-^^ '■'-^e support for the 
NASA/WTR Mission Support Office and the 6595th Aerospace Test Wing 

Furnishes four copies of changes to the icjnition and destruct wiring 

to L'^rir T"" '° '^^ Government Range Safety Office forty-five days prior 
to each launch. ' '^ 

u^n..nc /i^^r^'/" Operations Plan and Countdown Manual for each launch at 
onl and r^T.t II' ''"" '° ''" Government for approval within twenty- 

?n Jh . """^ ^"^ '^'^'* respectively, prior to the scheduled launch date. 
In addition, prepares a Countdown Manual for each launch at the Vandenberq AFB 

or orln'^h " ^°/^^G-— ^ for approval within fifteen working day ' 
prior to the scheduled launch date. 

In the performance of the field effort, the contractor completes the 

B^se'aTian 'pk'£ 'l''' ' "'^"^^ '"'^'^ ^^"^^'•" ^^ Vandenberg^Air or e 
Base and Wallops Flight Center handbooks for NASA Wallops Station 

fh. . n contractor maintains the VAFB sequencer and for the operation of 
the sequencer during all Scout activities involving the sequencer, SOP 6-3-2 
dress rehearsal, countdown and any special Scout tests required b^ the host ' 

Operates the Dynamic Balance Facility at Vandenberg AFB 
on . c.h I , ^""tractor provides a capability to launch a NASA/DOD Scout vehicle 
on a schedule of thirty calendar days after a notice for launch has been given 
dress rehearsal '^'xh' '" ^ ^'^^^^ readiness review meeting to be held following 
ZZluJl I l\ contractor presents in detail all major systems and all 

anomalies which have occurred in vehicle, GSE, and/or facilities during field 
processing. ~^ 

nnpr;,t!n 'd ^^"'^'^^''^^ ^ ' ^h Scout drawings, specifications, and Standard 

S^r^^t^d'by^NASA""' '''''''' '°^ '^"^^^^ ^"' '^"^^^ ^^°"^ ^^^-'" - 

Task J - The contractor provides technical assistance to the NASA and Centro 
Ricerche Aerospaziaii (CRA) in the review of program documentation, 

including launch complex maintenance and personnel proficiency mainte- 
nance drawing maintenance for S LC and S3T, concepts and plans, and 

launch complex modifications necessary to remain current to the Scout 
vehicle configuration. 



231 



ons , 



The contractor provides engineer inq supoort to a<;c:;<:t -,„a -^ 

incorporation of GSE modifications a'nd - inLnan^e ^f 'thf ^^ o Ta": ran^'^ 
assists in the maintenance of personnel proficiency of CRA. 

At the direction of the contracting officer, the contractor provides 
the services necessary to accomplish specific tasks assigned within tEe I imi- 
tations set forth in the areas described below: 

1 Operation concepts, including plans, schedules, and flow plans 
are reviewed in I, ne with established NASA/DOD Scout experience ThTs nc udes 
review of all plans for complex maintenance and personnel proflcienc^ includfnq 
configuration control to assure Scout compatibility. ^ 'ncludmg 

2. Support San Marco CRA Working Group Meetings 

wUh current llZ'l^TJZs'^ '''""""' °' ''' '""^'^^ '° "^ -P="^'^ 

5. Maintain San Marco operating procedures, drawings fSLC and ^-^T) 
and perform tasks to maintain personnel proficiency for Scoufvihidrope a [ 

l' ProvMe ^%P\- ^ '^ --^--tur ing tasks assigned by the Government. 

/. Provide technical support to CRA as directed by NASA Lanalev 
Research Center Scout Project Office in conducting San Marco launch operations 
in one or more of the following areas: operations 

a. Program Coordination 

b. Propulsion 

c. Guidance 

d . Mechan i ca 1 

e. Fluids 

f . Qual ity Control 

g. Electrical 
h. Operations 

^nH nr. ^' '''"''i'^^ ref u rb i shttien t of components returned from San Marco Range 
and procurement of new materials and spares as required to support operations 
and maintain current vehicle and GSE configuration. operations 

^^'^ "^ " Innr^°f f'""'^!; "^ '^f '''^ following training, i.e., certification, 
courses for the launch site personnel: 

Coaxial Cable 
Electrical Cable 
Electrical Connectors 
Potting and Seal ing 
Solder ing 
Pneumatics 
Hydrogen Peroxide 
Optical Equipment 
Propulsion and Pyrotechnics 

Training cycles of the above personnel were accomplished durina one 
(Wallops island and Vandenberg AFB) within a thrL-yea; period " "' "" 



232 



The Government provides training at Vandenberg AFB for launch personnel 
on dynamic balance procedures. 

Additionally, the contractor was responsible for providing certifica- 
tion of launch operation console operators at VAFB. 

Task L - The contractor managed the established Logistics Support Program which 
provided the necessary procedures, controls, and services to insure 
that adequate, serviceable and technically acceptable materials (spares- 
vehicles and GSE) were available for assembly, check out, and launch 
of Scout vehicles at Vandenberg AFB and Wallops Island and vehicle 
spares only at San Marco. 

The contractor maintained the established and authorized spares replace- 
ment system. A system of records, to provide a current perpetual inventory 
balance and condition status of all items from receipt to consumption, was main- 
tained . 

The contractor was responsible for directing the spares support system 
in accordance with the latest approved revision of the Scout Logistics Support 
System Standard Operating Procedures, report 3-30000/4R-87. 

Allocation and/or distribution schedules of all inventory items were 
maintained by the contractor for the complete spares inventory. Replenishment 
or supplementary requirements were submitted monthly to NASA Langley Research 
Center for review, approval and authorization as defined in Task M. The 
schedules and replenishment requirements were maintained including all the 
information previously submitted in the Quarterly Replenishment Requirements 
Report (QRRR) . The contractor was responsible for maintaining a requirement 
submission schedule that provided timely replenishment of all inventory items. 

For the performance of this task, the Government furnished the 
following at Wallops Island and Vandenberg AFB. 

Storage Space, 
Communication Services, and 
Office Space and Equipment. 

The contractor maintained vehicle spares for San Marco in the Scout 
Ouarterly Replenishment Requirements Reports (QRRR's). 

Task M - The contractor provided the services and materials necessary to 
perform the tasks listed below: 

1. Removed from storage and packing and crating of spare parts for 
shipment to field sites including receiving of sections and/or components 
from field sites. 

Z. Replenished supplemental spares parts and H2O2 as authorized by 
the contracting officer. 

3. In the event that spare parts which were unavailable from spares 
inventory were urgently required at one of the launch sites, the contractor 
was authorized to furnish such items from production, if available. Similarly, 



233 

items urgently required to support in-plant vehicle processing under the 
recertif ication concept were furnished from spares inventory, if available. 
Any item borrowed under either requirement was replaced through the Scout 
Logistics Spares Program. 

4. During the term of the systems management contract the contractor 
repairs, reworks, and/or modifies Scout vehicle and GSE parts, consisting of 
spares currently in the inventory for support of the Scout program as well as 
those that may be authorized during the period of the contract and any vendor 
components that malfunction during vehicle processing. This effort also 
includes the recert if icat ion of such spare parts and/or the corrective action 
necessitated by their shelf-life expiration. 

5. Under item 2 above, the contractor periodically prepares a list 
of the recommended spare parts including labor hour and material estimates for 
such list. These lists include replacement of vendor components that failed 
during vehicle processing and which were d ispos i t ioned as scrap. Upon direction 
from the contracting officer, the contractor initiates procurement action to 
obtain those items and quantities of spares as authorized in writing. As 

part of the documentation effort of Task L, the contractor maintains a listing 
of items authorized and procured hereunder, as well as the estimated cost 
thereof . 

Task N - The contractor's field personnel were responsible for launching Scout 
vehicles and maintaining the Scout Launch Complex (SLC) and Scout 
Standard System Test (S3T) and all associated Ground Support Equipment 
(including the Dynamic Balance Facility at Vandenberg AFB) and teleme- 
try stations. All equipment was kept in operating condition (per SPO 
Volume II, when and where applicable) and maintained current with all 
Scout vehicles and range requirements.'^^ 

The contractor's field personnel maintained status records of all GSE 
assigned to field sites and coordinated all material and component requirements. 
Material procurement, inventory control, shipping and receiving and reporting 
of overtime were performed in accordance with existing contractor field operat- 
ing procedures, as amended. 

In addition to those tasks set forth above, the Technical Representa- 
tive of the Contracting Officer, acting through the Scout Program Management 
Office at Dallas, Texas, assigned other tasks which utilized the services of 
the field personnel. All materials and/or special tools (other than handtools) 
which were required were furnished by the Government. 

The contractor's field personnel submitted a biweekly vehicle inspec- 
tion report (reference LTV report 3-1 5000/5R-231 ) listing the Test and Inspec- 
tion Report activity. The activity was separated into three groups titled 
Hardware, Procedures, and Ground Support Equipment. This inspection report 
denotes what Volume II Maintenance Procedures were performed and what Malfunc- 
tion Reports were initiated. 

The field sites maintained a drawing file of (one microfilm and one 
drawing) all contractor and subcontractor new and revised drawings related to 
the NASA/DOD Scout vehicle and its support systems. To further insure that 
up-to-date drawings were available to the launch teams, the contractor's field 



(l)Figure 87 charts a typical integrated field schedule that was performed by 

field, Dallas, and payload agency personnel. NASA personnel were also involved. 



234 



OF PCOK 




3 

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0) 
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1- 

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00 



235 



personnel updated a quarterlv index nf ;:»ii ^^^ • 

schenaticrfor^rbTNASA:'''' ''''"""'' "^^'"^^-^ ^^^^ '^oHowing working 

1. Launch Complex Functional Schematics 

2. H202 Fueling Unit (electrical and mechanical) 

fluid flowj '" '"''"'" (compressor room electrical and mechanical 

4. Launcher N2 Systems (launch arm and umbilical) 

°f this task, the fonL'Tlerl fir^i:hed. '"'"■ "" ''= Perfo™a„c. 

normal haid tl^fi^i'nad'a's-'Thr"'/"'" '='"" "" «"""'""'" -"P^ f°^ 

or profession") and''^! "^1 io/e'," ^ „Tat°v7F '^ ihr'-^'tV^'' = =^'" 
for the movement of heavy equiMent r^WhrL- . ' deluded services 

formed by the Government (mSA«aUopst and ^K ,'"' equipmentwas per- 
in accordance „,th the coLLtor .""e^^tlhltshed^'^nh'-^ri:: ^^hedut^^ ™^^' 
Ba'-« ,f;i,f^frJ)irj?fe^JfS^; ''' ""'' furnished-Jhe Oynamic 

-re furn^^hersfsfH; upon^:o:[;:c?or"re3:t'„°th1' f=^^'"'r" "^ changes 
Equipment maintenance Jaterials were provided by I^SA^r^ ?""*"""""• 
tests or additional tasl<s a. „,„ hi Proviaed by NASA. Material for special 

k Office ?h„^ /1l requested by NASA, was furnished by NASA 

'•-o contralto" ? ;i''°P;3:::erbn he'r'"''- °"'" '""^ "=' assigned'to *■ 
to the contractor to up^^ t pe sonne' mrte"™?"' -to!!?'' "''" """ ="'3-" 

!r!:.r!^!=i"-, ^--9e spac'ewas p'ovT^eTl^I^^p •in::^„\";-,rH,0, 

diivj h/i uuBchn ic devices ■ •-.^m^ aucM ds M2U2 

^.othins ?H,ofii^^;^^?if^. j;;:,=:-:tT:t^:rtLra:f :r°"=v^="=' 
jsA^;^crs^J:t:^?^qrt;:-t^""- -^ ^-^ ar„js:iir?echSr-f c:„%:r 

D- Direct Field Support Servirp<; rho f^ii« • 
ti^n^':??h'n^^r™r^^^^^^^- " =n^^ 

copies Of a stn^lf^t^^riJe":: ' la^r.rd^^l^r '"^^ "°'™= '^^ ^ 

b. Necessary reproduction services at Wallops Island 

c. Services of the machine, carpenter, and paint shops. 



more 



236 

d. Heater and air-conditioning serve i 1 lance, when the vehicle is 
in the shelter on a 24-hour-per-day basis, except during the contractor's 
regular work shift. 

e. Guard services at the launch pads, assembly area, and spin 
facility when required by local safety and/or security regulations. 

f. Operator and equipment for dynamic balance operations at 
Wa] lops I sland . 

g. Packing, packaging, shipping, and receiving of all Scout and 
Scout-related equipment. 

7. The contractor's field personnel also maintained all Government- 
furnished motor and vehicle shipping containers and handling dollies in a 
usable condition. Containers or dollies that become unusable, replacement 
was accomplished by separate contractual action. 

Task P - The Government made available suitable office space and equipment at 
Langley Research Center, Hampton, Virginia, as was required to accom- 
modate the personnel defined below. The contractor was not obligated 

to furnish more than twelve man-years of effort, including paid absences, in 

the performance of this task. The tasks included: 

1- Mechanical and Control Systems . Maintained liaison between the 
NASA Langley Research Center Scout Project Office, Wallops Station, Vandenberg 
AFB, and Contractor's Dallas facilities; performed design and layout for inte- 
gration of secondary payloads, and clarification of problem areas with vehicle 
and GSE; and performed other Government-approved tasks. 

2- Electronic Systems . Maintained liaison between the NASA/LRC Scout 
Project Off ice. Wallops Station, Vandenberg AFB, and the contractor's Dallas 
facilities; performed design studies for improvement of future hardware and 
circuitry of electronic systems on vehicle and associated GSE; investigated 
problems involving Radio Frequency (RF) transmissions at each range; and 
performed other Government-approved tasks. 

3. Propulsion Systems . Maintained liaison between the NASA/LRC Scout 
Project Office, Wallops Station, Vandenberg AFB, and the contractor's Dallas 
facilities; observed rocket motor tests; reviewed rocket motor flight performance; 
performed preliminary studies and evaluation as assigned by NASA/LRC Scout 
Project Office; and performed other Government-approved tasks. 

^- Rel iabi 1 ity and Qual i ty . Maintained liaison between the NASA/LRC 
Scout Project Office, Wallops Station, Vandenberg AFB, and the contractor's 
Dallas facilities; to integrate the Quality Control procedures for the vehicle 
and the rocket motors; and performed other Government-approved tasks. 

5. Operat ions . Maintained liaison between the NASA/LRC Scout Project 
Office, Wallops Station, Vandenberg AFB, and the contractor's Dallas facilities; 
provided coordination of Standardization and Configuration Control change 
traffic; investigated technical problems associated with field operations; and 
performed other Government-approved tasks. Appendix G describes other Scout Operations, 

"• Mission Analysis . Conducted parametric studies and analyzed Scout 
performance for unique mission requirements and determined the performance of 
suggested vehicle changes using available computer programer. 

7. Fl ight Data System . Analyzed telemetry records to determine 
validity, accuracy and quality, converted raw telemetry data to engineering 
unit displays, maintained a current data bank of past flight experiences; 
analyzed postf 1 ight data using the Scout Performance Evaluation Ascent Recon- 
struction (SPEAR) computer program, prepared and maintained "SPEAR and Scout 



237 

Data Handling" User's Manuals in a condition of readiness for operational 
use; and conducted studies to improve knowledge of vehicle performance and 
analyzed new instrument development and metfiods of data reduction. 

^- Computer Operations . Maintained, in an operational status 
Scout unique computer programs, Trajectory Optimization and Linearized Pitch 
Program (TOLIP) and SPEAR. Incorporated changes to the above programs as 
dictated by hardware and/or procedural changes of the vehicle and prepared new 
Scout computer programs as required for Langley Research Center computers. 

Task R - The contractor was contractually required to provide the services 
and materials necessary to perform special programs consisting of: 

Scout System Improvements 

Vehicle Payload Reass ignments 

Scout-Related Research and Development 

Reprocessing Support 

User Mission Peculiars 

GSE Design Changes 

Component Refurbishment 

Accuracy Prediction Studies 

Thrust Misalinement Measurements 

Feasibi 1 i ty Studies 

Anomaly Investigations 

Shelf Life Studies 

Special Instrumentation 

Motor Inspections 

Tests and Rework 

Scout-Related Studies 

Analyses 

Program Support 

Miscellaneous Requirements 

Tables LV I and LVII itemize Task R history during this time period. 

Task S - Special fixed price hardware and services individually contracted by 
the NAVPRO office for NASA were accomplished as required. These 
were similar to items in Task R, but were restricted to requirements 
that could be negotiated as a fixed price task. R&D effort was 
not included. 

Tables LV I ! I and LIX itemize Task S history during this time period. 

Task T - Includes all required production support of the Scout Program. Prior 
to NASI-I25OO this effort was not consolidated but included in most of 
the tasks. The contractor supplied all the off-site REPS as required 
during subcontractor manufactur ing . The contractor also supplied 
Engineering and Quality liaison for the required months of vehicle 
production to asbure compatibility of ail Scout systems and components. 
In addition, the contractor reviewed and advised disposition of all 
component and system dev iat ions and waivers, all malfunction reports, 
and all discrepancy reports. Material Rev iew Act ions (MRA's) and 
Test and Inspection Reports (TIR's). 



238 



OF POOR QUALiTY 



3336/ 
TASK TASK 
NO. CODE 



TABLE LVI - NASI -10000 R-TASK5 



DESCRIPTION 



JOB 
ORDER 



1. 



AAD 



2. 


AAA 


3. 


AAB 


h. 


AAC 


5. 


AAF 


6. 


AAL 


7. 


AAG 


8. 


AAE 


9. 


AAH 


10. 


AAJ 


11. 


AAK 


12. 


AAN 


13. 


AAM 


li). 


AAP 


15. 


AAS 


16. 


AAR 


17. 


AAT 


18. 


AAV 


19. 


AAW 


20. 


AAX 


21. 


ABB 


22. 


ABA 


23. 


AAY 


24. 


ABC 


25. 


ABD 


26. 


ABE 


27. 


ABG 


28. 


ABF 


29. 


AST 


30. 


ABX 


31. 


ABJ 


32. 


ABH 


33. 


ABK 


34. 


ABL 


35. 


ABP 


36. 


ABM 


37. 


ABN 


38. 


ABR 


39. 


ABS 


40. 


ABV/ 


41. 


ABW 


42. 


AC A 


43. 


ABY 


44. 


ACC 


45. 


ACB 


46. 


ACD 


47. 


ACE 


48. 


ACF 


49. 


ACG 


50. 


ACH 


51. 


ACJ 


52. 


ACN 


53. 


ACK 


54. 


ACL 


55. 


ACM 


57. 


ACR 


58. 


ACP 


59. 


ACV 


60. 


ACY 


61. 


ACT 



Scout Payload Separation/Ignition Timers, Survey & Select E6000Y/E7000Y/ 

E8000Y"-'-- 
Vehicle S-144 PAET Reentry, Payload Reassignment E4I440 

Vehicle S-173 Tests, San Marco E5173H 

Increased Payload Weight Capability for Scout Fourth Stage E7000R 
Destruct Receiver Power Switching E7000W 

Advanced Effort for Scout 4th Stg. Attitude Control Sys Study R1249"" 
Verification of X-258 igniter integrity E6001F 

Vehicle S-166 Special Test, GRP-A E5166H 

Rework and Retest of Vehicle S-163 E5163H 

Refurbishment of Misc. Components from Vehicle S-144 E4I44H 

Algol III Thermal Insulation Design E7000W 

Thermal Insulation Additions to Vehicle S-170 E5I70Q 

Support for Improved Guidance Hardware Study R1260"" 

Veh. Simulators, 2 1/10, 6 1/48 £ 2 1/32 Scale E6000R/E7000R 

Veh. S-193 & Sub. Command Destruct Rec'rs, Selection E7000W 

Verif. X-258 Igniter Integrity, X-Ray 3 ea. at HI/ABL E6001F 
Inventory and Tag GFE at WFC and WTR E41 440/E60000 

Algol III Jet Vane Effectiveness Prediction E7000W 

Scout Pressure Transducers, S-193 and Sub. E7000R 

Safe Arm Units, Veh. S-193 and Sub., Select 5 Qual. E7000(l 

NEMAR Output of Nominal Telemetry Data R1244-"" 

Redesign Third Stage Arming Relay Box, FAT £ Store E7000Q 

Determination of Roll Moment of Inertia E6000R 

Replacement of GFE Cables (4 ea. Endevco Cable Assys.) E6000H 
Special Instrumentation for Veh. S-184, MTS-A E6000R 

Design Improvement £ Testing of Nitrogen Regulators (Marotta) E6000R 
A-51 Heatshield Design and Modification, S-204, N-17 E7204H 

Integration of Nevj Scout Components in Veh. S-193 £ Sub. E7000Y 
Rework Three (3) Sets of Command Destruct Rec'rs, for WFC E7000W 
Modify and Reprocess Veh. S-l8l for AEROS-A Payload E6I8IH 

Improved Radar Beacon Antenna Assy. & Antenna, S-193 £ Sub. E7000R 
X-259 Rocket Motor Drop Test, No. HPC 129 w/Shipping Contnr E6OOOR 
Design Heatshield Ducting for Transit RTG (GFE 34-in -40 H/S) E6OOIJ 
Test Firing Overage O.6KS40 Spin Motors, S/N's 63301-001 £ 6409-1 E6OOOR 
Airborne Hi-Pres. Quick Disconnects, Compare Teflon Ring Seats E7000R 
Passive Roll/Yaw Comp. Simulators, Design, Fab. £ Test 2 Units E6OOIJ 



Transit RTG Payload, GSE £ Air Conditioning changes at VAFB 
Revision of Scout Motor Transportation Specification 
Cooling Air Sys. for A-404 and Field Support, INS-1 
ABV/ABVY Support for LaRC Scout Review 



E6001J 
E7000R 
E6182J 
E6000R 
E6000I 
E6182H 
E7000R 
E6OOOO 



Scout D Design Data and Range Safety Documentation 
Veh. S-182 Reprocessing Support, INS-t Transit RTG 
Spec. Instrumentation on S-I8I AEROS A and S-I85 ESRO IV 
Fabrication and Repair of Scout GSE, Da 1 las/WFC/VAFB 

Serv. to Monitor Qual. Test of 4th Stg, T/M Module Transmitter E6OOOF 

Algol III Hydroburst Test, Motor Mfr'd by Marquardt Corp. E7000W 

Castor IIA Propel lant. Long Term Storage Study by TC/H E7000R 

Aging Characteristics of Thixon AB-894 Primer Coat, Castor IIA E6OOOR 

Temp. Conditioning of Castor IIA S/N 127 to -20° below F. E6OOOR 

Test £ Insp. Castor IIA S/N 196 due to -20" below F Transport. E7197R 

Eval. of Gulton Timer on 4th Stg. Module, GFE S/N OO6 on Upper D E7000Q 

Motor Training Program for Field, WFC, VAFB, 6595th, CRA, etc. E6OOOK 

Design Review of High Pressure X-259 £ Light Weight Igniter E7000W 

Replacement of SD60En Initiators, X-259 Rocket Motor E7000R 

Refurbishment of Specific Sections of Veh. S-I78, SLV-IA E6I78H 

Scout GSE Design Changes and SOP Revisions E6OOOG 

UK-5 Fourth Stage Tip-Off Rocket, 0.6KS40 to Altai r III E6I87J 

Rewrite Catalog Section of Volume II of GSE Manual E6OOOO 

Algol III Motor Handling on Dolly, Reorientation, VAFB E7000R 

Transfer Personnel to Langley Support Office, 2 ea. E6OOOP 



TOTAL ''' 

14,151 

70,084 

34,622 

135,871 

29,932 

47,297 

1 ,046 

29,108 

15,060 

13,361 

13,947 

48,923 

17.413 

30,305 

12,836 

1,863 

8,464 

2,640 

5,821 

68,414 

1,386 

30,548 

8,140 

355 

44,560 

30,731 

5,397 

132,41 1 

9,813 

95.372 

19,628 

6,773 

21,934 

3.468 

6,944 

5,665 

13,069 

6,171 

36,325 

72,709 

34,043 

16,755 

51,036 

46,897 

1,495 

65,240 

14,611 

10,864 

5,362 

11,377 

12,316 

27,685 

12,130 

14,616 

20,412 

18,828 

1,786 

5,777 

896 

30,096 



■Total with 8.119 Foe. 
•180 Program J.O. 






OF POOR QUALITY 



239 



TABLE LVI - ^WS1 -10000 R-TASKS CONCLUDED 





3336/ 


TASK 


TASK 


NO. 


CODE 


62. 


ACS 


63. 


ACW 


64. 


ACX 


65. 


ADA 


66. 


ADB 


67. 


ADE 


68. 


ADF 


69. 


ADC 


70. 


ADJ 


71. 


ADH 


72. 


ADG 


73. 


ADM 


7't. 


ADD 


75. 


ADK 


76. 


ADL 


78. 


ADX 


79. 


ADP 


80. 


ADN 


81. 


AEE 


82. 


ADV 


83. 


ADY 


8h. 


ADT 


85. 


ADR 


86. 


ADS 


87. 


ADW 


89. 


AEA 


90. 


AEB 


91. 


AED 


92. 


AEC 


93. 


AEF 


9'.. 


AEG 


96. 


AEH 



DESCRIPTION 



JOB 
ORDER 



TOTAL* 



97. AEJ 



Modify Scout Fifth Stage for NPE Hawkeye Mission E6191J 

Scout Accuracy Prediction Studies, Vehs. Sub. to S-172 E6000R 
Incorp. High Pressure X-259 into Scout System E7000W 

SOP, Dwg. 6 Spec. Effort to Use Hewlett-Packard 5326A Counter E6000G 
SOP, Dwg. £ Spec. Effort to Use Fluke 8300A Digital Voltmeter E6000G 
High Pressure X-259, GSE Mods, and SOP Effort E7000W 

Scout GSE Design Changes, Design Effort Only E70000 

Design S Tooling Rqmts for New 25-in. P/L Transition Sect. E6000E 
Capacitive Discharge Ignition System, Fourth Stage R1277** 

Develop Math Model of NPE Hawkeye Spacecraft E6191R 

Support to SPEAR Computer Program, Post Flight Analysis R^lkk** 
Prod, of 10 min. P/L Orientation Film, Plus 1 Answer Print E7000R 
Installation of PCM Encoder into Two (2) Vehicles E8003R*** 

Installation of GFE Acoustic Sensor on S-188 E6188R 

Obtain X-259 Nozzle Attach Flange Deflection Data during Proof Test E7000R 
Feas. Study for Roll Stabilized Attitude £ Velocity Control Sys. R12't9*" 
Single Failure Point Investig., '♦th Stage Flight ACS H/W E6000W 
Feas. of Incorp. Hl-Energy Propel lant in Antares MB X-259 H/W E7000W 
Proc. £ Fab. of Scout GSE for Dallas, WFC and VAFB E70000 

Mod. of A-6225'tA Nitrogen Servicing Carts, 3 Dallas, 2 WFC, 2 VAFB E70000 
Design £ Fab. of ACS £ 5th Stg. GSE C/0 Equip, for NPE Hawkeye E6191J 



Thrust Misalinement Measurements on X-259 Motor at AEDC E6000R 

Rework of GFE Air Bearing E60000 

Feas. of Incorp. Hi-Energy Propellant in Altair IIIB H/W E8003R*** 

Provide Support for AEDC X-259 Motor Handling E70000 

Hydrotest Two (2) GFE X-259 Chambers in Vertical Position E7000R 

Replace Timers for P/L Sep. Sys. Test SEts, 19 Timing Units E70000 

Design/Fab. New W-k £ Altair IIIA Hoist Slings, 1 WFC, 1 VAFB E70000 

Retest of S-179 B and C Sections, A.F. P76-5 E6179H 

Proc, Test £ Store Spare ACS Components, NPE Hawkeye E6191J 

Furnishing of P/L Protective Shield, AEROS B E6186J 

Test Prog, for Shelf Life Ext. of BW 101270 Safe Arm Units E7000R 

Relining of A-6225'tA Dallas N2 Serv. Cart Tanks, 12 ea/3 carts E70000 
Unidentified Charges 

TOTAL 



23M3 

12,833 

24, 73^1 

8,879 

3,368 

26,663 

17,179 

23,237 

74,396 

7,386 

3,996 

3,062 

46,612 

5,088 

5,794 

113,914 

41,075 

104,274 

41,367 

12,619 

84,392 

2,635 

3,474 

68,392 

3,174 

4,325 

22,010 

23,688 

9,258 

46,541 

1,358 

2,955 

13,713 

19,135 

$2,462,953 



At the conclusion of a contract such as NAS1-10000, the unfinished tasks were extended in time 
only, so as to have continuity with the replacement contract (NASI -12500) . The use of these 
tasks for urgent requirements was ideal, as the delay in contractual requirements were minimal 
because of the unique Scout task system. This system was instrumental in having Scout accomplish 
its program below budget. Task R has been used successfully from its inception through Phase VI, 
and is presently used in Phases VII and VIII contract NAS1-16200. 



-■Total with 8.119% Fee. 
-••'''180 Program J.O., Total $258,402. 
^^^-^Phase VIII Total $121,436. 



2it0 



TABLE LVll - NASI -12500 R TASKS 



OF POOR Q'^ 





3384/ 


TASK 


TASK 


NO. 


CODE 


1. 


AA 


2. 


AB 


It. 


AD 


5. 


AE 


6. 


AF 


7. 


AG 


8. 


AL 


9. 


AJ 


10. 


AK 


11. 


AH 


12. 


AM 


13. 


AN 


^^. 


AP 


15. 


AR 


16. 


AS 


17. 


AT 


18. 


AV 


19. 


AW 


20. 


AX 


21. 


AY 


22. 


BA 


23. 


BB 


21). 


BC 


25. 


BD 


26. 


BE 


27. 


BF 


28. 


BG 


29. 


8H 


30. 


BJ 


31. 


BK 


32. 


BL 


33. 


BM 


ih. 


BN 


35. 


BP 


36. 


BR 


37. 


BS 


38. 


BT 


39. 


BV 


1(0. 


BW 


itl. 


BX 


42. 


CA 


't3. 


CB 


kl^. 


CC 


US. 


CO 


46. 


CE 


47. 


CF 


48. 


CG 


49. 


CH 


50. 


CJ 


51. 


CK 


52. 


CL 


53. 


CM 


54. 


CN 


55. 


CP 


56. 


CR 


57. 


CS 


58. 


CT 


59. 


CV 


60. 


CW 


61, 


CX 


62. 


DA 


63. 


DB 


64. 


DC 


65. 


DD 



DESCRIPTION 



JOB 
ORDER 



Refurbishment of Wallops Island Standard Launch Complex E7000R 

Backup Air System for Vandenberg AFB, CA, Add. of 2nd Compressor E7000R 
Incorp. of GFE Ign. £ Instrum. Kits in 3 Vehs. E6192Q/E7194Q/E7196Q 
Supplemental Range Safety Data for NPE Hawkeye Mission ^q ^' j 

Delta Post Flight Corporation of PCM Encoders, S-I86 & S-I88 E8000W 
Altair III Alternate Qual.Test Fac. (USAF RPL Edwards AFB) Spi n Fixt.E7000R 

.. _^n / /- . i\ I- ._! IJ_J n .. Ct^^:„ M^-.i- •i.-amAt-lt- TdQf E7002R 



Mitair III HiLerndLt:y.uai.ic3L ia«-.\vj^ni <*■•- ■ — -■-' 

X-258 (6 yrs old) Embedded Boot Strain Measurement Test 

Modification of Ignition Battery Simulators 

Delta Effort, Due to 4th Stg., ACS & H.P. X-259 

Fab. Verticality Sensor Mounting Bracket 

Incorp. of 38 New GFE Power Supplies in Scout GSE at Dallas 

TOLIP Computer Program Modification 

Test Fire One (1) Altair III Motor at Edward AFB, CA 

Improved Environmental Control System (ECS) for Scout Pav'oads 

Shelf Life Test First-S Second-Stage Initiators, Spec. 304-788 

Modify VEGA Radar Beacon, Spec. 305-765 



E7002R 
E7000R 
E6I9IJ 
E6000R 
E70000 
E7000R 
E7000Q 
E6000R 
E6000R 
E7000R 



Modify VEGA Radar Beacon, bpec. :)U5-/o5 cIT^qd 

S-178 Flight Spin Anomaly at 4th Stg. Sep. , Addendum to Post Fit Rpt E617BK 



Vought Support at UTC/CSD of FW-4S Motor Buy, 6 mos 

Scout SOP Revisions, S-193 & Sub. Changes, Vols. I S II 

Add. 8 Twisted Shielded Pairs, Umbilical Cable Wire, VAFB Complex 

48-Pound (6 ea.) Thrust Control Mtrs Rework Prog., 4 ea on S-191 

Install 5 Checkout GFE GSE at VAFB, Includes Mod. Kits, for S-191 

Prep, for Fit. Two (2) BE-3A9 Motors, S/N's AN09/003 & AN09/010 

Design 6 Fab. 2 X-259 Tunnel Tab Pull Test Tools, 1 WFC & 1 VAFB 

Command Destruct Receivers Test S Rework, 9 MCR-151C-1 

Hewlett-Packard HP5326A Counter Rework, 7 Dallas, 3 WFC, 3 VAFB 

Series 200 E-Section Separation Clamp Study 

Scout Fourth Stage PCM Telemetry System Development 

Contractor Instruction to Govt. Personnel of Scout Systems 

Fourth Stage Ignition Timer Check Modification 

Install Conduit Sys. £ Wiring (Explosive Proof) at VAFB, DBF-21 

Antares MB Nozzle F 1 ightworthi ness Program 

Static Test Firing of X-259 GFE Motor S/N NIB 211 

Altair III Motor Dome Blanket 

Shelf Life Extension of 20 P/N 23-002981-8 Explosive Bolts 

Scout Standard Operating Procedure, Volume VII (New SOP's) 

BE-3A9 Motor Nozzle Plugs, Motor S/N's AN09-003 & AN09-010 

Assy. Two (2) Fourth Stage Modules, S/N's 005 and Oil 

Postf light Data Computer Program Revision, PFDATA 

Proc. and FAT of One (1) 23-004214-1 Regulator 

Design 6 Fab. 2 Castor II GFE Hoist Beams, Dwg. S SOP Revisions 

Furnish Six (6) 1/20 Scale Scout Simulators 

Re-hydrotest Three (3) Antares MB Motor Cases at Hl/B 

Demo. High Energy Propel lants in Altair III Motor ™-''S 

Demo. High Energy Propellants in Altair III Motor (TEM-640) 

Display Vehicle, Assy. Full Scale Launch Veh. on Transporter, WFC 

Mod. to D Section Cooling Air in S^T at VAFB 

Mod. of Scout Vehicle S-179, Thiokol Safe/Arm Units 

Determ. of Feas. for Polar Launches from WFC, F-1 Profile 

Scout Third Stage PCM Telemetry Trade Study 

Scout Nozzle Data Book, Phase III 

Attitude Test of 60-Pound Motor 

Ground Support Test Set 4th Stg. Capacitive Discharge Ign. Sys. 

Design Loads and Testing Criteria for Upper Stages. Phase I 

Static Test One (1) GFE Altair III Motor at AEDC 

Inspection of X-259 Rocket Motor. S/N HI B- 307, UK-5 

Autodestruct Module Design Improvement 

Development of Fourth Stage Ignition System 

Study of Replacement for Scout Third Stage Guidance 

S-191 Flight Anomalies Investigation. NPE Hawkeye 

Castor II Shelf Life Extension Program 

Aging Characteristics of Thixon AB-894 Bond Promoter, 

VAFB GSE Remodifi cat ions Req'd to Process Veh. S-179, 

Backup Air Supply at VAFB 



4-yr 
A.F. 



E7000Q 
E7000R 
E70000 
E7000(J 
E70000 
E6I9IQ 
E70000 
E70000 
E 70000 
E7000R 
E8000W 
E7000K 
E70000 
E7000R 
E7000Q 
E 7000(1 
E7000Q 
E7000(i 
E7000G 
E6I9IJ 
E7000(i 
E7000R 
E7000a 
E70000 
E6000R 
E7000(l 
E8000W 
E8OOOW 
E7193R 
E7000R 
E6179(1 
E80OOR 
E8OOOW 
E7000R 
E6000R 
E8OOOW 
E7000R 
E70000 
E6187Q 
E8OOOW 
E8OOOW 
E8OOOW 
E6I9IW 
E70O0R/E7002R 
Test E7000R 
P76-5 E70000 
E7000R 



TOTAL' '' 

29,237 
6,773 
13,422 
1,235 
10,333 
21,417 
1,881 
30,598 
105,827 
3,286 
24,668 
21,975 
6,855 
77,657 
1,784 
1,657 
5,814 
13,928 
13,545 
16,501 
18,913 
31 ,212 
5,388 
3,977 
12,706 
1,835 
4,010 
62,092 
7,042 
15,432 
8,813 
28,616 
21,730 
5,479 
2,523 
44,116 
2,743 
1,653 
5,807 
7.657 
7.407 
1,035 
72,779 
126,562 
107,973 
20,578 
4,186 

495 
28,602 
50,106 
65.031 
14,295 

4.382 
32,642 
17,576 

6,361 
35,007 
91,701 
19,882 

4,226 
62,608 

2,854 
11,314 
53.668 



■Total with 7.9895; fee. 



241 



?^?£;^^ 



TABLE LVII - NASI -12500 R TASKS CONTINUED 





3384/ 


TASK 


TASK 


NO. 


CODE 


66. 


OE 


67. 


DF 


68. 


DG 


69. 


DH 


70. 


DJ 


71. 


DK 


73. 


DM 


74. 


DN 


75. 


DP 


76. 


DR 


77. 


DS 


78. 


DT 


80. 


DW 


81. 


DX 


82. 


EA 


83. 


EB 


84. 


DC 


85. 


ED 


86. 


EE 


87. 


EF 


88. 


EG 


89. 


EH 


90. 


EJ 


91. 


EK 


92. 


EL 


93. 


EM 


94. 


EN 


95. 


EP 


96. 


ER 


97. 


ES 


98. 


ET 


99. 


EV 


100. 


EW 


101. 


EX 


102. 


FA 


103. 


FB 


104. 


FC 


105. 


FD 


106. 


FE 


107. 


FF 


108. 


FG 


109. 


FH 


110. 


FJ 


in. 


FK 


112. 


FL 


113. 


FM 


114. 


FN 


115. 


FP 


116. 


FR 


117. 


FS 


118. 


FT 


119. 


FV 


120. 


FW 


121. 


FX 


122. 


GA 


123. 


GB 


124. 


GC 


125. 


GD 


126. 


Gt 


127. 


GF 


128. 


GG 


129. 


GH 


130. 


GJ 


131. 


GK 


132. 


GL 



DESCRIPTION 

Nozzle for High Energy Propellant Modified Antares MB 

Study to Define Scout Derived Vehicles 

Handcarry S-I87 Guidance Components to San Marco Range, UK-5 

Support to NASA/LaRC Anomaly Investigation, S-189 ANS-A 

Base A Battery Cell Improvement, Yardney PM15 

Wind Tunnel Prog 1/8 Scale Model, Scout w/Strap-on Motors 

S-189 Flight Anomaly Investigation, ANS-A 

X-258 Rocket Motor Shelf Life Extension Program., S/N HIB-208 

Final Flight Report, S-I87 UK-5 

Extension of TX-463-1 Pyrogen Shelf Life 

Design £ Fab. Heatshield Support Assy. £ 4th Stg. Handling GSE 

Spec. Test of Guid. Components £ Detailed Eval. of Diodes, ANS-A 

Rework of 4 GFE 48-lb Thrust Control Mtrs to 60-lb Config., SAS-C 

Anal, to Determ. Feas. 

Anal, to Determ. Feas. 



JOB 
ORDER 

E8OOOW 
E8OOOR 
E6I87X 
E6I89W 
E7000W 
E8OO3R 
E6189W 
E7002R 
E6187D 
E7000R/E7002R 
E 70000 
E6I89W 
E7194Q 



of Incorp. High Energy Propellant Algol III E8OOOW 
of Incorp. High Energy Propellant Castor I I A E8OOOW 



Environ. Control System (ECS) for Scout Pay loads, VAFB Effort E70000 

Environ. Control System for Scout Payloads, Remaining WFC Effort E70000 

Inspection of 8 GFE X-259 Motors by Hl/B E7000Z 

Add. of Battery Access Doors to H/S's, 3 34-in £ 3 '42-in, DAD-A E7196J 

Fab. of Fwd. Relief Boot, High Energy Propellant Antares MB E8OOOW 
Algol I IB Shelf Life Extension Program E70OOR/E7OO2R 
Guid. Comp. Insp. £ Retest, Diodes Proc. , S/N 78 Intervalomtr Rework E7000Q 

DAD Payload Interface Support E7196J 

Vehs. S-I79 £ S-192 Guid. Components Insp. £ Retest E61 79R 

GSE Mods, for Guid. System Environmental Tests £ SOP's E7000R 

Proc. of Altai r MIA Shelf Life Extension Materials E7000R 

Veh. Component Processing Flow - Mech. Sys. E7000R 

Veh. Component Processing Flow - Guid. Sys. E7000R 

Veh. Component Processing Flow - Control £ Hydraulic Sys. E7000R 

Veh. Component Processing Flow - Control Sys. £ H2O2 Sys. E7000R 

Veh. Component Processing Flow - Propulsion Sys. E7000R 

Veh. Component Processing Flow - Ign. Oestruct £ Power Sys. E7000R 

Veh. Component Processing Flow - R.F. Components E7000R 

Nozzle Fab. for Antares MB Motor with XLDB Propellant E8OOOW 

Fab. of Antares MB Motor with XLDB High Energy Propellant E8OOOW 

Static Test Firing of Antares MB with XLDB High Energy Propellant E8OOOW 

Perf. of s2eT, Vehs. S-193 - S-197 £ S-199, after Programing E7000F 

Study/Feas. of Replacing Guidance System Rate Gyros E7000W 

Mod. £ Test of 52 GFE W-lb Thrust Control Mtrs to 60-lb Config. E7000Y 

Scout Historical Summary Report, Revision to Vol. M E7000R 

Scout Family Tree Performance Study, 17 Configs. £ 12 Missions E7000R 

TOLIP Computer Program Implementation on NASA Computer E7000R 

Performance Review, Rpt. 23.532, Vehs. S-I78, S-186-S-191 E7000R 
Pref light and Postf light Report £ Analysis, SAS-C E7194C/E7194D 

Mod. £ Test of Intervalometer, S/N 079-085 E7000Y 

Mod. £ Test of Intervalometer, S/N 086-092 E7000Y 

Fabrication of Two (2) Fin Tips E7000Y 

Study to Reduce Damage Potential to Veh. Due to Rain Exposure E7000R 

Scout Engineering Training Film, Tech. Oriented, 1 Orig. £ 2 cys E7000K 

Feas. of Eliminating Single Failure Point Sources, Guid. Sys. E7000F 

TIP-MI Mission Heatshield (A-^iOB) Fit Checks E7197B 

UK-6 Mission Fourth Stage Module Kit Assy., Mockup £ Fit Check E7198J 

PCM Telemetry Package Development E8OOOW 

Scout Automatic Checkout Study E8OOOW 
One Engr. £ One Consultant to S.M. Range, Repair Cracks in Launcher E7000J 

Prepare Pref light Brochure, TIP-MI E7197C 

Prepare Pref light Brochure, DAD-A E7196C 

Pref light Planning Report £Preflight Review, DAD-A E7196C 

Prefiiyhl Fianning Report EPreflight Revipw. TIP-MI E7I97C 

Support to Scout Shelter Improvements, WFC £ VAFB E70000 

Paint Dummy Heatshields (to Aid S/C Cleanliness Rqmts) , WFC £ VAFB E7000V 

A-509 Heatshield Fit Check, DAD-A E7196B 

Furnishing of Scout Simulators, 1/48 £ 1/72 Scale E7000R 

UK-6 Misc. Hardware, Payload Support Rings, etc. E7198J 

Design, Fab., Test £ Integrate 2 Heatshield Handling Fixtures E70000 



TOTAL* 

23,990 

8,585 

'(,550 

90,744 

4,491 

104,512 

57,250 

31,775 

38,062 

5,640 
37,556 

5,024 

4,777 

93,788 

9'(,95I 

89,919 

100,487 

5,199 
10,231 

6,817 
111,834 
70,484 
18,108 
24,428 
80,294 
39,096 
'(3,215 
82,433 
21,651 
77.491 
60,792 
58,831 
40,677 
72,258 
104,529 
15,724 
34,823 

4,228 
54,515 
18,0*48 
26,686 

6,8'.9 

15,134 

61,268 

104,253 

104,405 

5,959 

4,683 

34,235 

154,023 

3,962 

2,0't5 
16,539 
31.773 
16,635 

1.927 

2.657 
27.151 
15,973 
20,309 

5.812 

4.3'<4 

10,616 

13, '(93 

203, '166 



*Total with 7.989% Fee. 





338V 


TASK 


TASK 


NO. 


CODE 


133. 


GM 


135. 


GP 


137. 


GS 


138. 


GT 


139. 


GV 


l^iO. 


GW 


1^41. 


GX 


Ii.2. 


HA 


l^tS. 


HB 


lit it. 


HC 


US. 


HD 


\he. 


HE 


\hl. 


HP 


litS. 


HF 


\U3. 


HH 


150. 


HJ 


151. 


HK 


152. 


ML 


153. 


HM 


15't. 


HN 


155. 


HP 


156. 


HR 


157. 


HS 


159. 


HV 


160. 


HW 


161. 


HX 


162. 


JA 


163. 


JB 


I6it. 


JC 


165. 


JD 


167. 


JF 


169. 


JH 


170. 


JJ 


171. 


JH 


172. 


JL 


173. 


JM 


Mh. 


JN 


175. 


JP 


176. 


JR 


177. 


JS 


178. 


JT 


179. 


JV 


181. 


JX 


182. 


KA 


183. 


KB 


185. 


KD 


186. 


KE 


190. 


KH 


191. 


KK 


192. 


KL 


193. 


KM 


195. 


KP 


196. 


KR 


197. 


KS 


198. 


KT 


200. 


KW 


201. 


KX 


202. 


LA 


203. 


LB 


20(1. 


LC 


205. 


LD 


207. 


LF 


208. 


LG 



242 



TABLE LVIl - NASI -12500 R TASKS CONCLUDED 



DESCRIPTION 



OF POOR QUAl 



.ITY 



JOB 
ORDER 



Testing to Establish Max. Quantity of Environmental Testing Limits E7000R 

Vendor Survey to Replace 1950 Guidance Sys. for Scout Vehicle E8003U 

Payload Support for GP-A Payload E7193J 

Static Test Firing of X-258 S/N l'l6 Motor at HI/ABL E7002R 

Design & Fab. 3 Portable Digital Ordnance Test Sets E70000 

Demo. /Test Fire Altair ill with High Energy Propellant (TP-H-3335) E8003R 

Inspection Monitoring Case Fab., Altair III w/High Energy Propel 1. E8003R 

Heatshield-to-Payload Fit Check, GP-A E7193B 

Incorp. of Accumulated Mods. (Rework 6 Insp.), GFE S-179 E6179H 

Installation of GFE Instrumentation Kit into S-198 E7198Y 

Scout Standard Operating Procedures (SOP), Demonstration Phase I E7000G 

Generalized Lifetime Data and Accuracy Predictions E7000B 

Component Improvement Review E7000F 

Insp. of 3 Castor IIA Motors, S/N's 193, 382 & 38't, at VAFB E7000Z 

Study Prog. Advanced High Energy Propellant Altair III, Phase I E8003R 

Hazard Analysis of a Shuttle Payload Propulsion System E8003U 

Design & Proc. Antares MB Igniter Shipping Containers, 18 each E7000Z 

Painting Interior of GFE Heatshield A-509, DAD-A E7196J 

Environmental Protection for Scout/Shuttle Auxiliary Stages E8003U 

Vol. Ill SOP, Short-haul Motor Transportation Procedures E7000G 

Fuel On-board vs. Pressure Drop Relationship, Vehs. S-193 " S-207 E7000R 

Rework of Castor Motor Drill Fixture 23-000026-1, S/N 9060li7 E7000V 

Final Flight Report, S-195, TIP-II E7195D 

GP-A Umbilical Sep. Test & Environ. Control Alarm Sys., WFC E7193J 

Roll and Yaw Compensation Units, Nonrecurring Effort Prior to Fab. E7002Y 

Relining ^l Nitrogen Serv. Cart Tanks by SOC-CO, N2 Cart S/N 1005 £70000 

Vendor Survey £ Selection of H2O2 Bladders, Phase VIII Vehicles E8OOOR 

S-179 lith Stg. T/M Sys. -Design, Remove Storage, Instl. £ C/0 E6179H 

Retest of S-179 Components, A.F. P76-5 E6179H 

S-179 Retest and Payload Reassignment, A.F. P76-5 E61 79B/C/D/H/J 

S-201 Wallops Station Polar Launch Impact Areas, HCMM E7201J 

Fin Switch Deletion in S3t and SLC E7000G 

Overall Scout Program Review, Presentation at NASA/LaRC E7000F 

Stage Impact Dispersion Based on Flight Experience E7000R 

Antares IIA Rocket Motor Hardware Modifications E7000Z 

Rework £ Reinspection of Antares IIA Nozzles and Igniters 

Marotta Regulator Improvement Evaluation Program 

TIP-II I Heatshield Ejection Test 

Rewrite Volume I Standard Operating Procedures 

Range Safety Requirements for Standard Operating Procedures 

Engineering Training Film, 1 Answer Print £ 6 Copies 

Qualification Firing of Antares IIA (Athena) Motor 

Performance Capability Study of TIP-II I Launch from WFC 

Spec, for Environmental Control Units 

Launcher Components Maintenance/Replacement Verification 

Scout Guidance System Performance Criteria 

Mods, to Interface KECO Spacecraft Coolers with GSE at VAFB 

Perf. Cap. Study, MAGSAT Launch w/New 3rd £ Itth Stage Motors 

S-192 3rd £ hVn Stage Motor Change 

UK-6 E Section Clamp Test 

Proc. of 200 2nd Stage £ ^lO 3rd Stage H2O2 Silicone Bladders 

Nondestructive Testing £ Inspection of GFE Castor IIA, S/N 177 

Phase VIII Engineering Changes 

Lanyard £ Electrical Disconnect Bracket Separation Tests 

Fab. of Roll/Yaw Compensation Units, 3 ea. P/N 23-003760-1 

Resident Representatives at Vendor Facilities 

Critical Process Review, Scout Components (90 Comp. Incl. Motors) 

Insp. of 3 GFE X-258 Motors, S/N's -l'48, -151, -152, at HI/ABL 

Maintenance Procedures for Airlog Dollies 

UK-6 Fit £ Ejection Test, GFE Itth Stg. Module S/N 012 Fit Instl. 

Structural Test Antares MB Nozzle Graphite Phenolic Taped Insert 

TIP-II £ TIP-III Spacecraft Dynamic Loads Analyses 

Hot Pressed Carbide Materials, Survey £ Evaluation 

Unidentified Charges 



E7000W 
E7197H 
E7000G 
E7000G 
E7000R 
E7196W 

E7197J 
E70000 
E8OO3Y 
E8OO3Y 
E70000 
E72038 
E6192Z 
E7I98R 
E7000Y 
E7000Z 
E8000E 
E7000E 
E7002Y 
E7000T 
E7000F 
E7002Z 
E7000G 
E7I98H 
E7000R 
E7195B/E7197B 
E7000R 



TOTAL 



TOTAL " 

? 35,965 
123,336 
't3,651 
1(1,651 
1(5, 6118 
103,230 
5,393 
5,705 
8,071 
2,62i( 
23,56i( 
10,796 
30,1(52 
2,883 
1(8,081 
62,71(7 
8,656 
3,367 
1(9,1(16 
i(,302 
12,031 
503 
1(5,798 
11,210 
18,963 
6,119 
3,908 
1(1,91(7 
7,1(11 
106,210 
6,51(3 
6,205 
1(9.303 
7,511 
1(0,786 
171.906 
35.1(70 
20,116 
37.560 
1.898 
i(0,08i( 
50,Mk 
3,1(60 
6,73i( 
16,559 
1(3,629 
12,1(07 
1,1(142 
66,085 
7.071( 
21(0.823 
11,125 
58.676 
21,500 
bh,2kk 
62,119 
9.530 
21,929 
3.963 
1(5.011 
13.572 
39.918 
8.322 
10,11(7 

$6,1(28.588 



'•Total with 7.989?; Fee. 

>wcE6l79Z-$28,736; E6192Z-$18.987; E7193Z-$28,737; E7197Z-S27.986 
E7198z-$18,986; E7Z00Z-$28.737; E7201 Z-$18,987; E7000Z-$750. 



Call No. 


1 


2 


3 


4 


5 


6 

7 


8 

9 
10 


11 


12 


13 


14 
15 
16 



243 

TABLE LVIII - NASI -10000 S TASKS 
Description ___^ Auth. Price 



Ultrasonic Inspection of Castor I lA Motors 
No. 181, 182 and 183 

Accumulation, Inspection, Packaging, and 
Crating of San Marco-C Pyrotechnics 
Rework and Testing of San Marco Separation 
Systems 

Provide 32 RMS Finish on certain FW-4S Motor 
Components 

Furnishing of Installation and Removal Tool 
for Rocket Motor Igniters 
Furnishing Scout Vehicle Long-Lead Items 
GSE Modifications required to support the 
SAS-B Operation 

Procurement of Algol Ml Terhmal Insulation 
Recertif ication of Scout Vehicle S-1 70 
Castor II Shelf Life Extension Problem and 
Aging Study 

Integration of S/N-1 Fourth S-Band Module 
and S/N042 E-Section on Scout 
Purging and Vacuum Drying of Vehicle 166 
at Wal lops Island 

FW-4S Rocket Motor Shelf-Life Laboratory 
Testing Program 

Modification of A-63 Heat Shield 
X-Ray of X258 Motor HIS at ABL 
Ultrasonic Inspection of Castor II Rocket 
Motor S/N 187 at Wallops Island 

17 Training in use of Ultrasonic Inspection 5,775 5 775 
Equipment 

18 Refurbishment of Scout B-Section 9,325 9 315 

19 Procurement of Battery Cells 1,200 1*200 

20 Fabrication of Payload Protection 2,568 2*568 

21 Furnishing Ultrasonic Standards for Algol III 6*34l 6*341 
Motor 

22 Retuning of Command Destruct Receivers 10,125 10 125 

23 X-258 Rocket Motor and igniter Shelf-Life 40,979 kO 979 
Extension Program 

24 Furnishing of Five (5) Special Instrumentation 59,810 59,810 
Kits for X-259 Rocket Motors 

25 Modification of Scout Vehicles to Acconmodate 43,116 43,116 
New Safe/Arm Units 

26 Furnishing of Scout Launcher Base-A Support 8,525 8 525 
Pins 

27 Repair of Algol II! Motor Raceway Drill Fixture 7,469 7,469 

28 Assembly of Scout Fourth-Stage Ignition and 
Telemetry Systems 

29 Furnishing of Long-Lead Items 4,955 4,955 



$ 2,686 


$ 2.686 


989 


989 


11,604 


11,604 


2,740 


2,740 


11,203 


11,203 


11,586 
19,500 


11,586 
19,500 


18,223 

135,850 

47,050 


18,223 

135,850 

47,050 


3,431 


3,431 


3,053 


3,053 


57,428 


57,428 


532 
4,028 
2,240 


532 
4,028 
2,240 



OF POOR QUALrr/ 

Ikk 

TABLE LVMI Coneluded - NASl-10000 S TASKS 

Call No. Description Auth. Price 

30 Procurement, Fab., and Installation of Scout 
Ground Support Equipment Changes 

31 Incorporation of GFE Ignition & Instrumenta- 
tion Kits into 'j^-^u\ Vehicles 

32 Provide Services to Conduct Acceptance Testing 
of GFE 

33 BE3A9 Rocl<et Motor Shelf Life Extension Program 

34 Procurement, Fabr ication and Incorporation of 
Algol III Modification Kits 

35 X-4 Payload Ignition Support 

36 Tone and Signal Generators 

37 Fourth-Stage Ignition and Telemetry System 

38 Furnishing of (75) Thermistor Assemblies 

(1)t0TAL task S $7^7,866 $7^+7,866 



$ ^^,359 


$ 44,359 


8,162 


8,162 


6,192 


6,192 


U7,900 
29,490 


47,900 
29,490 


981 

54,696 

1,301 

17,775 


98I 

54,696 

1,301 

17,775 



(^Task S is similar to Task R but is used instead of R when enough history is 
available to negotiate a fixed-price agreement. If any unknown variables 
apply to a specific task then the cost reimbursable Task R is selected as 
the proper task. 



245 



TABLE LIX - NASI -12500 S TASKS 



TASK 
NO. 



MOD. 



S-001 


16 


S-002 


16 


S-003 


16 


S-00i» 


16 


S-005 


16 


S-006 


28 


S-007 


28 


S-008 


'43 



DESCRIPTION 

Mod. of Veh. S-I89 to Accept the Algol Ml 
Furnishing of Scout Explosive Bolts 
Furnishing of 3 N. Atlantic Phase Angle Voltmeters 
Furnishing of Ablative Cork for Scout Vehicles 
Fab. and/or Replacement of Scout Tooling at Dallas 
6 ea. 200 Series 6 6 ea. 25 Series Add. P/L Sep. Sys . 
9 Algol Ml Mod. Kits, 66 Fin Tips £ 62 Jet Vane Assys, 
Fab. and/or Replacement of Scout Fin Tools 



JOB 


NEGOTIATED 


ORDER 


FIXED PRICE 


E6289Y 


$ 11,855 


E7000Y 


37,125 


E70000 


8.900 


E7000Y 


S,3kk 


E7000V 


39 , 1 1 8 


E7000Y 


168,852 


E8OOOY 


921,^8 


E7000V 


37,000 



TOTAL 



$l,230,9i»2^'= 



Task V - The contractor maintained and kept in calibration the Government- 
furnished Ground Support Equipment (GSE) as listed in Table LX, and 
located at the contractor's Dallas, Texas, facility in accordance 
with Q,CPP-0-005C. 



TABLE LX - GOVERNMENT FURNISHED GROUND SUPPORT EQUIPMENT (GSE) 



Descr ipt i 



on 



(1) Telemetry Test Set 

(2) Guidance Test Set 

(3)1 Destruct/Receiver Test Set 

(k) Continuity & Electrical Test Set 

(5) Radar Beacon Test Set 

(6) Flight Readiness Test Set 

(7) Hydraulic Control Test Set 

(8) IRP Test Point Box 

(9) PVE Filter Simulator 

(10) Valve Test Point Box 
(n ) J-Box 5. Cable Plant 
(12) Greer Hydraulic Cart 
en) No Servicing Cart 

(14) Servo Analyzer 

(15) Payload Separation Test Set 

(16) Rate Table 

(17) Ign it ion/Destruct Simulator 

(18) Dividing Head 

(19) Bladder Leak Test Set 

(20) Portable Test Set (331059999101) 



Qty, ea 

2 
2 
1 
1 
1 
1 
2 
2 
2 
1 
2 
2 
2 
2 
1 
2 
1 
2 
1 
1 



"Supplemental Agreement '»3. 



246 
TABLE LX Concluded - GOVERNMENT FURNISHED GROUND SUPPORT EQUIPMENT (GSE) 



(21) Portable Test Set (331-500001-2) 

(22) Valve Simulator 

(23) IRP Leak Test Hose 
{2k) Rate Gyro Simulator 

(25) Portable Counter Oscillator 

(26) Base "A" Adapter 

(27) Sfiorting Connector Set 

(28) N2/H2O2 Hose Assembly 

(29) H2O2 Hose Assembly 

(30) Head Cap Pressure Simulator 

(31) PVE Test Point Box 

(32) Battery Simulator (LD-601173) 

(33) Battery Simulator (321-00076) 
(3^) Battery Simulator (321-00077) 

(35) Battery Simulator (321-00078) 

(36) Transition "E" Simulator 

(37) ign i t ion/Destruct Simulator 

(38) Base "A" Flyaway Simulator 

(39) Umbi 1 ical Simulator 
{kO) Auto Destruct Test Set 
(41) N2 Fi 11 Hoses 

{hi) VSWR Test Set 



All remaining S3T equipment was placed into Government storage at 
the contractor's Dallas facility. The contractor had use of specific compo- 
nents within these stored S3T equipment during the contract period. 

The contractor maintained all Scout assembly, machine and detail 
tooling required in the performance of all Scout program efforts and contracts. 
The term "maintenance" as used herein is defined as all effort necessary to 
insure that the above-mentioned tooling is kept in a condition suitable tor 
the fabrication, assembly, and installation of all Scout hardware in accor- 
dance with applicable specifications and/or drawings. In the event the con- 
tractor considers an item of tooling in need of replacement, immediately upon 
such determination the item was appropriately tagged, the basis for the deter- 
mination adequately documented, and the NASA notified. Hence, atthe expira- 
tion of the contract, all tooling was either in acceptable condition or tagged 
and controlled by the contractor as in need of replacement. 

In the event the Government determined that the contractor should 
effect replacement of any Scout assembly, machine, and detail tooling required 
in the performance of a 1 1 Scout program efforts and contracts, such replace- 
ment was accomplished by separate contractual action. 

Task W - Support for failure ihvest igat ions required by the NASA were accom- 
plished by separate contractual action in the form of a Contract Call 
Notification. Such call actions were serially numbered, setting 
forth the supplies and/or services which the Government desired, the 



247 



estimated dollar amount thereof, and the allni-m«o*- ^ u . 
contractor was obligated sublect to th! f f?^ * *° ''^ ^^^'"9^^- The 
the call, to furnish the services and/nr ^""^ '""Nation set forth in 
and to submit a cost proposal thL^J.-!!!^''' '!' ^P^^'^'^d therein, 
call,. These separate con? actual acMn'''", '.^^ ''""^ specified in the 
tigation. removal of parts and est no T'"'"' '" ^''°'' '°' '"-^ 

stallation effort was^cc^^ptJshed b " ont a^^L'^'act-^'^'"" '"' ''^'"- 
the appropriate task thereof Thoe ^oni^ractual action pursuant to 

and/or hardware that were ava i llbfe f^'^"'"*'' ^"''^y^tems. systems, 
were made ava i lab le .rrrr -i '!^'!._^'^°'". ^P^--" ^' production invento, 



the appropriate task thereof Th^.^ contractual action pursuant to 
and/or hardware that were ava i llbfe f^'^"'"*'' ^"''^y^tems. systems, 
were made available arGFE!" appropH^t:''^" °^ Production inventory 

.•ncentive'provi:l^^".Tt\o^\"hXris^"o;^in",u^ 

the Scout Project Office includes the cost. Zl r ^T^^-^^tua I ly in Task W. 

of failure investigations. The per formal! Tt -^^.'^ ^ ^' '^ '' ^ the negative 

receiving the award are outllned'as ^Ho^:.. '"'''°"^ ^"' ^'■'^^'■- ^- 

^^- ^^Nily oT-^~^^^^l^^'.J^-^^\P^rfor.snce was evaluated on 
cessfully. For purposes onva'Ltin'rrde^'ree^T ''"•'' '■^'' ^'"'■°" -- 
t.on from nominal of inertial veloc ty att^tndT ""'"l^" '""^"' ^^^ ^^'-•■^- 
and orbital inclination at burnout of ^^hefl.^: '"^'■"'' ^"s^^t-path angle, 
and solar probe missions and thTvarlation ? '^^ ''"' "'^^ ^°'" ^"'^^ °^bi 
altitude, inertial f 1 iaht-oath annl. ^^ °^ "°^'"^' °^ inertial velocity 
was used for reentry an^d^^^^H ^^^b: :iss::r'' ^"^'^ '' '^^^ ''^'^ ^---' 



General Ground Rules 



, ^- P'''°'' to each launch, the contractor submitted to NASA a 
Preflight Planning Report which cited the nominal values of the parameters 
Identified in paragraph 1. together with the variation in each for a 99 7 ner- 
cent probability, determined from calculations based on past flight historv 
The contractor also noted the mission parameters of particular interest to th. 
payload user. Th.s document was submitted for approval no lateJ than thirty 

'otor'datl \LITh°\^'' ''''"' '"° "T^" '''"'■ '■"^"'P^ °^ ^^^^ l^^t mission Ind 
motor data inputs, whichever occurred last. 

m^nt -.!,• ^: ^^""^^^^ ^^f^'^^ ^^''vered the payload into the proper environ- 
ment, within the limits established by the variation from nominal L a 99 7 
percent probability, were normally considered successful. However, shoulda 

Hnrino f?- h! l^^^'u'"" ^"^ ^^'^'' ^^-T^P^'^ent, Subsystem, or system occur 
during flight which potentially jeopardized the success of the spacecraft 
mission, the Award Evaluation Board may consider such failure or malfunction 
of" u ce^rr' l^ degree of success of the launch. The adjustment in decree 
whi^h th ! '"^^^ ^^''"''' °' malfunction was based upon the extent to 
BoIrH ^'^^^^"^•■^^tor, ,n the judgment of the members of the Award Evaluation 
Board met reasonable standards in the design, fabrication, reliability and 
quality assurance practices, and systems management with regard to the part 
component, subsystem, or system which failed or malfunctioned 



248 



c. 



r 1 .• :> ^^f '^""^^^^ "^'^^^ deviated from 3-sigma limits, the Award 
Evaluation Board determined the degree of success attained. 

d- Missions which clearly failed to achieve required performance 
through any fault of the vehicle were considered unsuccessful. 

,^ u^' ,"'^5'°"^ aborted in flight as the result of any contingency 
which could be shown was not a vehicle malfunction was not considered a 
failure; the Award Evaluation Board determined the degree of success based 
on the time of flight at which abort occurred. Should a failure or malfunc- 
tion which potentially jeopardized success of the spacecraft mission occur 
prior to the abort, the degree of success was adjusted as stated above. 

f. The effectiveness with which the contractor identified the 
mission parameters of particular interest to the user, and gave special atten- 
tion to these parameters in planning the mission, were considered in assessing 
the degree of success of the launch. 

g. Space tracking data, based on a least six orbits, were used 
to determine orbital performance. Space tracking data, range tracking data, 
vehicle performance telemetry data, and/or payload telemetry, were used to 
determine solar probe performance. Range tracking data, vehicle performance 
telemetry data, and/or payload telemetry data were used to determine reentry 
performance. Depending upon the site from which the vehicle was launched 
vehicle performance was determined in accordance with the following: 

Wallops Launch. For flights during which Wallops FPS-16 
tracks the vehicle to final-stage burnout, and provides usable data, this data 
was used to determine performance. |n the event that Tallops FPS-16 did not 
track to final-stage burnout, the Spandar data was obtained at this point, then 
Spandar data was used to determine performance. 

^ . .. Vandenberq Air Force Base Launch . Any FPS-16 radar, which 
tracks to final-stage burnout, and provides usable data, may be used to deter- 
mine performance. In the event that usable tracking data was not obtained, 
vehicle performance telemetry and/or spacecraft telemetry data was considered. 

S^" Marco Launch. The San Marco AN/MPS-26 radar is used to 
determine performance if satisfactory track to final-stage burnout is obtained. 
In the event that usable tracking data was not obtained, vehicle performance 
telemetry and/or spacecraft telemetry data was considered. 

Task X - All shipping requirements are recorded under this task by the NASA 
Scout Project Office. Figure 88 shows the Scout Program shipping 
expenditures through FY 1978. Scout motors had to be transported as 
per a defined specification. Appendix L includes this 1973 specifi- 
cation. 

Task Y - All vehicle hardware contracts are recorded under this task by the NASA 
Scout Project Office, as noted in table XXXIII. 

Task Z - All motor hardware contracts are recorded under this task by the NASA 
Scout Project Office, as noted in table XXXIII. 

Figure 89 shows the chart used by the Scout office describing the task designa- 
tions. ^ 

The LTV Scout Program Organizations is shown in figure 77. This chart covers 
all the managers for the above- listed management tasks. During the course of 
the Scout Program personnel changes were made. However, most of the managers 
nad many years of Scout experience. 



249 



OF POOR QUALITY 



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250 



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251 



OF POOR QUALITY 



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253 



CHAPTER 7. LAUNCH SITES AND FACILITIES 



PRECEDING PAGE BLANK NOT FILMED 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



254 



Figure 16 defined the Scout launch sites that house most of the Scout facili- 
ties. Table LX I itemizes the facilities that are both Government and contrac- 
tor owned. 

NASA had total responsibility at the Wallops Flight Center launch site which 
is shown in figures 90 and 91. The Air Force was responsible for the Vandenberg 
Air Force Base Scout launch site which is sketched in figure 92. The Range at 
both sites was the responsibility of other Government groups, not the Scout 
Project Office. Figures 93 through 101 are photographs from the Scout launch 
s i tes . 

Task N previously described the operations of the launch sites. The facilities 
were updated to the latest state of the arts only if cost effective. The 
Scout was the only space launch vehicle that operated from Wallops Island and 
San Marco. Figure 102 shows the payload field flow processing plan utilizing 
the facilities. Figure 103 shows a Scout vehicle on the Mark-ll launcher at 
Wallops Flight Center, 

A typical vehicle operations plan is outlined in Appendix G. Figure 10^+ shows 
lift off of Scout S-181 at the Vandenberg AFB launch site. 




Figure 90.- Scout launch facility at Wallops Flight Center 



C 



0RIG5WAL PAGE IS 
OF POOR QUALITY 



255 



TABLE LXI - FACILITIES 



1 . Launch Complexes 

a. Wallops Station (Figs. 17(a) & gi) 

Launcher §1 & Shelter, figs. 21, 

22, 90, 94, & 95- 
Launch Consoles (two sets) (fig. 93) 
Standard Scout System Test Equipment 

(fig. 21). 
Transporters (figs. 21 & 22). 
Assembly Buildings (Range) (fig. g6.) 
Motor Storage Facilities (Range) 
Motor Handling Equipment 
Spin Faci 1 i ty (Range) 
Closed Circuit Television & Intercom 

(Range) 
Mobile Telemetry Station (fig. 99) 
I nterplant Cabl ing 
H2O2 and N2 Facility (fig. 100) 
Heating-Cooling Facility 
Blockhouse (Range) 
Spares Stock Room 

b. Western Test Range (Figs. 17(b) & 92 ) 

Transporter (figs, 21, 22) 
Launcher and Shelter (figs. 21, 22, 

9^ &95). 
Range Users Building (fig. 96) 
Spin Faci 1 i ty (fig. 97) 
Mobile Telemetry Station (fig. 99) 
H2O2 and N2 Facility (OSB) (f ig. 1 00) 
Standard Scout Systems Test Equipment 
Ordnance Assembly Building (test sets) 
Spares Stock Room 
Operational Support Building (test 

sets) 
Motor Storage (Range) 
I nterplant Cabl ing 
Heating (Air Force) 
Blockhouse 
Launch Consoles 



Storage Sites 

Hawthorne Nevada-Motor Storage 

Langley Research Center 

Research Faci 1 i ties 
Test Faci 1 i ties 

Contractors' Plants 

a. LTVAC/Vought Missiles and 

Space Company 

Test Checkout Equipment 
(Two-and-a-half sets) 
Twin Assembly Lines (fig. 101) 
Jigs 

Spares Stock Room 
Vehicle Storage Area 
Minneapolis-Honeywell Facilities 

b. Aerojet General Corporation 

Manufacturing Facilities 
Test Stand Facilities 

c. Hercules Incorporated 

Manufacturing Facilities 
Test Stand Facilities 

d. Thiokol Chemical Corporation 

Manufacturing Facilities 
Test Stand Facilities 

e. United Technology Corporation 

Manufacturing Facilities 
Test Stand Faci 1 i ties 

A.E.D.C. 

Tullahoma Test Facilities Available 



256 



Ol^^S'.v 



OF POOR Cp^^^ ^ 



WALLOPS STATION LAUNCH 

^;; .;;.; ^i; :• encompasses EXPENDED STAGE IMPACT 
AREAS FOR CIRCULAR ORBITS BETWEEN 
300 AND 700 N. M. ALTITUDE 

^^^ BERMUDA CORRIDOR. LAUNCH AZIMUTHS 
BETWEEN 109 AND 126 NOT ALLOWED 




MAIN BASE 

CAUSEWAY 




-70" -60" -50" -«• -30* 

EXPENDED STAGE IMPACT AREAS - WALLOPS STATION 



M) ASSEMBLY SHOP NO. 3 

(21 ASSEMBLY SHOP NO. 4 

(3) HEAVY EQUIPMENT STORAGE AREA 

(4) DYNAMIC BALANCING FACILITY 

(5) TV CAMERA STATION NO. 2 
(6t BLOCKHOUSE NO. 3 

(7) LAUNCH AREA NO. 3 .ERMINAL BUILDING 

(B) LAUNCH AREA NO. 3 

(9) PAYLOAD WORK FACILITY 




i3^fT»^ 



1. ASSEMBLY BUILDING 

2. BLOCKHOUSE 

3. WINCH BUILDING 



7. LAUNCHER 



4. SHELTER 

5. LAUNCH PAD 

6. UTILITY BUILDING 



Figure 91.- Sketch of Wallops Island Launch Complexes. 




257 



ORIGINAL PAGE B 
OF POOR QUALITY 




1. ASSEMBLY BU'.LDINr. 

2. TERMINAL "'JiLDiNG 

3. LAUNCHED 

4. LAUNCH PAD 



5. WINCH ASSEMBLY 

6. SHELTER 

7. UTILITY BUILDING (O.S.B.) 
6. BLOCK HOUSE 

9. A G E BUILDING 







iMF'ACT 




i ■ I ■ ' 



KXPKNDF:n STACt: IMPACT AHKAS - WTR 



■^^^^^ 



Figure 92.- Sketch of Western Test Range Launch Site. 



258 






OF POOR QUAi-iTY 




MODULAR ENCLOSURE SYSTEM A 
OPERATORS CONSOLES 



UNIT 2 
GUIDANCE 



UNIT 3 
CONTROL 



UNIT 4 

LAUNCHER 

CONTROL 



UNIT 5 
POWER 
CONTROL 



UNIT 6 
PAYLOAD 



UNIT 6A 
PAYLOAD 




MODULAR ENCLOSURE SYSTEM B 
SUPERVISORS CONSOLES 



UNIT 15 
NASA TEST 
REPKESEN- 
TAl IVE 
(NT°.I 



UNIT 9 
GUIDANCE 



UNIT 10 
CONTROLS 



UNIT II 

TEST 

DIRECTOR 



UNIT 12 
INSTRUMENT 
SYSTEM 
MONITOR 



UNIT 13 
PAYLOAD 
INSTRUMEN 
TATION 



UNIT 13a 
PAYLOAD 
MONITOR 



UNIT 14 
IGNITION 
DESTRUCT 
MONITOR 



UNIT 16 
RANGE 
SAFETY 



UPPER LEVEL 




Figure 93.- Wallops Island Launch Complex Blockhouse Consoles. 



- V 



ORIGINAL PAGE IS 
OF POOR QUALITY 



259 





. 


ti^ 


■ '>: 


' il 




Figure 9^.- Movable shelter exterior - typical. 




Figure 95.- Movable shelter interior - typical 



260 







Figure 96.- Range Users Building WTR. 



CONTROL 
BLOCKHOUSE 



mm 



SPIN BUILDING 



1 






'■ ^-ftsfeT^^ 



Figure 97.- Spin Test Facility - WTR. 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



ORlGll^Al. PAGE \2^ 
OF POOR QUALITY 



261 




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TWO 10 TON 
BRIDGE CRANES 



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Figure 98.- Assembly Building - Wallops Island. 



ORlGlNAi: PAGE 
BLACK AND WHITE PHOTOGRAPH 



262 




Figure 99.- Telemetry mobile ground station (T/M van) 




Figure TOO,- Fueling room servicing equipment - typical 



263 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPK 




#^ 




Figure 101 .- Vehicle Assembly Area 



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ORIGINAL PAGE 
BUCK AND WHITE PHOTOGRAPK 



267 



CHAPTER 8 - SCOUT FINANCIAL DATA 



268 



The Scout Program received its first funding in 1959. Appendix H consists of 
the Scout Status of Funds memo which was sent monthly to NASA Headquarters. 
It has been updated monthly as the program continued, and has been updated to 
its most current status. Table LX I I shows the history of the Scout funds and 
is divided into Phases as defined on page 1. Table LX I 1 I itemizes all the 
Scout funds by fiscal year. 

EXPENDITURES 

Development expenditures, exclusive of institutional support (nomenclature 
changed to RPM), through fiscal year 1976 were approximately $3^-^ million. 

Vehicle hardware costs through fiscal year 1976 were $112.0 milllon(^), detailed 
as fol lows : 



(1) Phase II - $0.96 million per vehicle, 

(2) Phase III - $1.42 million per vehicle, 

(3) Phase IV - $1.18 million per vehicle, 
(k) Phase V - $1 .19 mi 1 1 ion per vehicle, and 
(5) Phase Vl - $1.31 million per vehicle. 

Table LXIV details the total obligations by fiscal year in the fiscal year 
obligated for all Scout funds. Table LXV itemizes the obligations of each 
phase VI vehicle by task-job orders. Table LXV I details the hardware only 
obligations for each vehicle. Table LXV I I summarizes the obligations of 
Phase VI by task for each user. Table LXVIII details the obligations in 
Table LXVII for each vehicle. Table LXIX details the obligations not included 
in Table LXVI. This table presents the non-hardware effort of the major contracts 
Tables LXX through LXXV I I I detail by year the activity of each fiscal year funds 
of the Scout program through 1979. 

USER COSTS 

The basis for the data in all the preceding tables is analyzed from the data 
calculated as contract prorations. The cost of each deliverable item in each 
contract was prorated from the total cost and assigned a job order that automat- 
ically computerized the cost to the correct launch vehicle and mission. This 
was accomplished for services, software, and research, as well as hardware. 
According to the ground rules (the NASA/DOD agreements) certain nonadditive 
costs were not to be paid by the DOD; and the cost of the field team and field 
services was derived by the use of a formula as illustrated in the next sec- 
tion of this chapter. The rules of charging non-United States users changed 
drastically as the Scout Program continued. Costs such as depreciation, 
percentage of research and development, audit costs, civil service salaries, 
NASA overhead, travel, and other similar costs in addition to direct costs were 
included. ''°> 



(a) $15.03 Million are included for Phase UN 

(b) This text is concluded on page 328 . 



269 



ORIGINAL PAGE (3 
OF POOR QUALITY 



TABLE LXII - HISTORY OF SCOUT FUNDS, BY PHASES 



PHASE I 

Devel opment-Scout 



FUNDS 
(Mi 11 ions) 



LAUNCHES 



NASA OTHERS No. Initial REMARKS 



U.^ 



7-1-60 Two operational 

payloads and four 
other successful 
probes and reentry 
launches . 



Deve 1 opmen t-Motors 
Algol MA 

Antares I 
Antares I I 

Altair II 

Vehicle Improvements 
Cold Separation 
Velocity Control 
3^-inch Heat Shield 
New Jet Vanes 



2.2 

1.0 
1.3 



0.1 
0.7 
0.1 
0.2 



Wallops Launch Complex & G.S.E. 3.3 

PHASE II 

10 Production Scouts k.O 

Air Force Special Scouts 

WTR Launch Complex and G.S.E. 2.3 

PHASE III 

18. 1 



14 Production Scouts 



Motor Development 
Altair III 



Castor 1 1 



Sustaining Engineering 



Motor Prediction Study 

Algol Nozzle Redesign 

E-sect ion 

Air Transport Study 

Standardization 

Castor II Design Completion 

Evaluation Vehicle 

G.S.E. 



0.1 



1.3 



6.7 



0.5 
0.5 
0.3 
0.2 
]A 
0.3 
0.3 
0.7 



0.5 



8.2 
0.6 
2.7 



** 



8-31-62 Upgraded first stage. 

First flight S-]]k. 
7-1-60 X-25if, 

3-29-62 Upgraded third stage, 

X-259. 1st fit. ST-9. 

6-28-63 Upgraded fourth stage, 

X-258. 1st fit. S-113. 

3-1-62 First Flight on ST-8 

4-26-62 First Flight on S-111 
8-31-62 First Flight on S-114 

7-1-60 Mark I & Mark I I 
complexes 



10 4-26-62 (3 NASA) Includes 

spares . 
4 5-24-62 Direct purchase of 

vehicles by Air Force 
4-26-62 Mark II complex. 



5.4 14 



12-19-63 (11 NASA) Includes 

recert i f ication pro- 
gram and spares: 
also S-I3I evaluation 

8-IO-65 Navy developed fourth 
stage (FW4S). First 
flight on S-I3I 

8-IO-65 Upgraded Second Stage. 
First f 1 ight on S-I3I 

7-1 -63 Includes new relia- 
bility program and 
incentive contract, 

7-20-64 

8-10-65 First flight on S-I3I. 



8-10-65 
8-10-65 



■>''lncludes prototype. 
-•wVDi rect DOD Funding. 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLE LXI I Concluded 



270 
HISTORY OF SCOUT FUNDS, BY PHASES 



FUNDS 

(Mill ions) 

NASA OTHERS 



LAUNCHES 
NO. INITIAL REMARKS 



PHASE IV 

Vehicle Hardware (Ol-OO) 
(25 Vehicles) 

Mission Mods (01-04) 
Supporting Activities (Ol-OO) 
Product Improvement (O3-OO) 

TOTAL 25 PRODUCTION SCOUTS 

PHASE V 

Vehicle Hardware (01 -00) 
(15 Vehicles) 

Mission Mods (01-04) 
Supporting Activities (01-00) 
Product Improvement (03-OO) 

TOTAL 15 PRODUCTION SCOUTS 

PHASE VI 

Vehicle Hardware (Ol-OO) 
(15 Vehicles) 

Mission Mods (01-04) 
Supporting Activities (Ol-OO) 

Product Improvement (03-OO) 



TOTAL 15 PRODUCTION SCOUTS 

PHASE VI I (Projected) 

Vehicle Hardware (Ol-OO) 
(15 Vehicles) 
Mission Mods (01-04) 
Supporting Activities (Ol-OO) 

Product Improvement (O3-OO) 



TOTAL 15 PRODUCTION SCOUTS 
TOTAL THROUGH PHASE VII 



11.8 17.7 



0.5 


0.3 


9.3 


6.8 





0.2 



21.6 25.0 



15.5 



35.2 



10.1 



2.4 



5.2 



8.8 



30.0 24.5 



1 0. 5 I 5. 6 



25.7 3^-6 
147.0 7^.7 



24 11-18-65 (10 NASA) Includes 
Spares & Tool ing 



7-1-65 Management & Software 
7-20-63 Algol II Nozzle 



10 4-27-68 



0.9 


0.2 




17.2 


2.5 


11-1-67 


1.6 


0.1 


9-8-67 



10-9-69 



8-16-71 



(13 NASA) Includes 
Spares & Tool ing 



Management & Software 
Includes Fifth Stage, 
Velocity Package, Navy 
Roll Yaw 



(8 NASA) Includes 
Spares & Tool ing 



0.7 


0.3 






17.9 


15.1 


11-1-70 


Management £ Software 
& Range 


1.3 


0.3 


5-31-67 


Includes BE-3 Fifth Stage 






2-19-68 


S-Band 






2-18-70 


42-inch Heat Shield 



5-8-75 (6 NASA) Includes 
Spares & Tool ing 






5 


1.0 






11 


9 


18.0 


11-1-74 


Management, Software 
S Range 


2 


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6-26-69 
2-18-70 


Includes Algol 1 1 1 
Jet Vanes 



12-22-70 Command Destruct 



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TABLE LXIV(d) • SCOUT ffiOGAAH R £ OBLIGATtONS 
(Fisc«l Year Obligated 






ORIGINAL FA 

OF POOR QUALITY 



FISCAL YEAR FUNDS FY 1971 & PR I OR 

REIMBURSABLE- I HTERHAT I OWAL 

AEROS-B {k8l) 

FY 197'* 
** FY 1975 
FY 1976 
FY 1977 
FY 1978 

SUBTOTAL 
ITALY (Jt83) 



FY 


1977 




FY 


1978 




FY 


1977 


(STOl 


FY 


197» 


(STO) 


SUBTOTAL 




UK- 5 


(■.8;) 





FY 19714 

FY 1975 

FY 1976 

FY !971t (STO) 

FY 1976 (STO) 

SUBTOTAL 



" 1973 



FY 197lt 



FY 1975 



'1 ' ?76 



" 197T 



FY 1979 



5 808.770.12 5 1,675.872.81 5 19.639.85 5 -73.962.65 $ 209.679.8? S 5 S 2 61.0 000.00 

9611.631.79 -3. 5811.16 2't,721.57 158.285.09 195.915.52 5,265.23 1 .3l<5,235.01t 

22,<>l<8.02 1,831.15 -162.00 21.,617.17 

20,500.29 -81.65 20.1*18.61* 

609.88 227.79 837.67 



s 183.363.00 S 

269.1*81t,15 210.162.00 

no. 000. 00 

100.000.00 



S 51.870.76 S 68.01 5 6.I4I6.23 

18.636.02 lt6,363.9 



661*, 525. 00 



s 11,307.15 



73,1*31.00 



S 51.870.76 5 18,704.03 $ 717,305.21 $ 11.307.15 5 73,1*01.00 S 



S 808,770.12 5 2,6li0.50l..60 $ 39.003.71 5 -1*7,1*09.93 5 388,303.25 S 196.1.1*3.75 5 5.1*93.02 s 1*. 031 ,108.52 



$ 183,363.00 
1*79.61*6.15 
110.000.00 
100.000.00 



S 183,363.00 S 1*79. 1*81*. 15 5 210.162.00 $ 873,009.15 



58,325.00 
65.000.00 
11. 307. 15 
661*. 525. 00 
73 .''3 1.00 

872,568.15 



UK-6 (1*83) 



FY 


1975 


FY 


1976 


FY 


197T 


FY 


1977 


FY 


1978 


FY 


1978(STO) 


FY 


'979 



SUBTOTAL 
REIMBURSABLE-INTERNATIONAL TOTALS 



19.55 
1.266,53 S 



S 30,610.81* s 67.369.61 5 

16.51* l*.98 1.071.889.05 1,219,376.21 
1,305.00 -6.1*3 -1,298.57 

3,875.60 137,l*l*3.86 -1,0.00 

1*5,050.81 1,673,360.00 

10.000.00 

. 111*. 266. 32 



l,y/1.5i* $ 3lt.l'81*.99 S 1 .321 .1*51*. 81 $3.016,962.53 
% 860,61*0.88 $ 2,659,208.63 $ 73'. 495. 00 ! -3l*,78l.2l< J 679,552.21* % 1 ,996,382. JL $ 1 ,337. 6i7.i;f 



S 98.100.00 

2,292,553.36 



11*1.273.1*6 

1 ,718.1*10.81 

10.000.00 

111*. 266. 32 

S 1*, 371*, 509. 95 

S 10.151,215.77 



■-^FY 1960 
■•^FY 1961 

FY 1962 

FY 1963 

FY 1961* 

FY 1965 

FY 1966 

FY 1967 

FY 1968 

FY 1967-6-9-0(tfAFBl 

FY 1969 

FY 1970 

FY 1971 

FY 1972 

FY 1973 

FY 1971* 

FY 1975 

FY 1976 

FY 197T 

FY 1977 

FY 1978 

FY 1979 



; 5.603.061.78 

1.115.874.28 

10.273.856.95 

6,932,001.20 

977.381.00 

2.71*5.320.1*1* 

2,025.81*8.58 

9,009,953.83 

2.128,252.81* 

679. '81 .on 

1*81.. 533. 71 

4.345.21+ 



-2,908.00 5 2,908.00 



-13,754.00 
-3,182.00 

2.581,589.74 
755,657.91 



13.754.00 
3.182.00 



-112.42 S 



9 - I IZ.',£ 9 III .•ti 

397,334.64 5-2,666,762.78 2,025,087.99 -2,5)1,946.99 S 426,594.91 $2,729,148.66 S -798,641.86 i 796,520.07 
3.834,269.94 -300,391.20 349,194.45 696,092.06 -10,697.75 10,697.75 -582.013.89 575,265.03 



1,020.931.00 

1,988,639.98 

23.541.17 

45,962.20 



-210.350.53 210,350.53 



-400,098.07 

448,334.83 

13.095.38 

1,700.001.31 



•1.420.279.02 

-326,229.72 

-32,638.14 

1,676,178.40 

741 ,579.96 



84.970.00 

66.316.35 

-442.48 

242.768.75 

40,746.94 



31.451.00 

-8.354.98 

-717.620.79 

494,387.33 

386.765.12 

12.003.52 



390.545.37 

46.529.02 

-244.026.15 

54.032.71 

1,227,981.43 

-468.91 



1.074.896.97 

-0.23 

-81 .98 

4,860,527.57 

-603.701.07 

3,997,962.74 

1,803,809.63 
196,736.48 



230,057.57 

-22.654,92 

81.98 

-113,991.17 
530.155.00 

,012.817.50 

481.850.98 

*,S80.513.04 

534.653.20 



5.603, 
1.115, 
10.273, 
6.932 

977: 

2.745, 
2.025. 
11.988, 
7,456, 

679 

484 
1,020 
1,613 

579 
64 
7,403 
1,216 
4,640 
11 
2.289 
5.177, 

534 



061 .78 
874.28 
856.95 
001 .20 

,381 .00 

320.44 
847.58 
878.21 
327.14 
.281.00 
,533.71 
.931.00 
,355.28 
.852.85 
,151.00 
,837.92 
453.93 
638.73 
534.61 
.407.78 
,249.52 
,653.20 



$41,979,710.85 



3,336,775.26 $ 7,330,522.93 5-1.205,820.53 $ 2,802, H30.97 5-1,171,033.42 $ 614,528.36 54,218,187.05 $9,949,494.36 5 6.979,633.28 $74,834,429.11 



FY 1961 
FY 1962 
FY 1965 
FY 1971 
FY 1975 
FY 1977 
SUBTOTAL 
AEC 

FY 1963 (AL) 
FY 1963 
FY 1974 



5 1 ,800.000.00 

7.899,999.12 

3.348.00 



5 2.600.00 



S 9.703,347.12 S 2,600.00 5 



$ 26,563.60 
2,371,000.00 



65.000.00 



5 65,000.00 



$ 220,000.00 



S 94.000.00 
5 94,000.00 



$ 1.800,000.00 
7.900.000.00 
3,348.00 
2.600.00 
65.000.00 
94.000.00 
S 9,864,948.00 



5 26.563.60 

2,371 ,000.00 

220.000.00 

s 2,617,563.60 



3 REIMBURSABLE TOTALS 554.:30.621 .57 $3.339.375.26 5 7.330.523.815-1.205.820.53 5 3.087,430.97 5-1.171.033.42 5 614.528.36 $4,218,187.05 510.043.494.36 $6,979,633.28 5 87.316,940.71 



5201.484.866.86 518.527.291 .14 519.022,096.14 $16,143,109.10 515,942,228.44 513,262, 24J. 63 52,766.388.40 517W8. 072.94 528,180.893.60 521,149.333.07 5353.796,525.32 



-609A Progra*]!. 
i-*lncludes STS direct. 



ORIGINAL P^^f ,i.^ 

276 OF POOR QUAUTY 

TABLE LXV(a) - PHASE VI OBLIGATION OF FUNDS BY VEHICLE - FOREIGN AGREEMENTS 

(NASA) 

J.O./ TRUST FUNDS SAN MARCO REIMBURSABLE 

TASK 185 188 . 190-000 186 1 90-483 TOTAL 

A $ 318,928 $ 330,9it3 $ 318,938 $ 310,900 

B 45,612 13,218 6,071 4,474 

C 16,066 22,022 12,210 14,495 

D 45,309 40,821 36,032 43,086 

E 151,969 213,125 145,013 186,477 

F 184,566 166,448 145,018 155,637 

G 67,762 63,963 53,240 61,857 

H 183,254 229,824 148,245 276,687 

I 842,510 881,610 778, 606 

J 6,069 1,358 

K 

L 

M 64,286 77,544 47,341 76,467 

N 393,228 424,650 424,650 

39,500 39,500 39,500 

p 

Q 60,872 54.715 318,533 

R 

s 2,398 

T 34,858 38,216 27,450 26,161 

U 68,600 94,400 107,420 

V 52,804 62,804 96.266 86,088 
W 105,286 100,000 100,000 100,000 
X 20,000 20.000 14.428 19,981 

Y 546,759 541,379 539,550 561,676 
Z 387,048 402,074 376,796 400,758 

TOTAL $3,629,217 $3,823,325 $2,068,996 $3,994,811 



$ 


$ 1.279,709 





69.375 





64,793 





165,248 





696,584 





651.669 





246,822 





838,010 





2,502,726 


720,897 


728,324 

















265,638 





1,242,528 





118,500 











434,120 











2,398 





126,685 





270,420 





297,962 





405.286 





74.409 





2.189.364 





1,566,676 


$720,897 


$14,237,246 



277 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLE LXV(b) - PHASE VI OBLIGATIONS OF FUNDS BY VEHICLE - NASA 



TASK 



180 



181 



183 



184 



187 



A 


$318,938 


$318,938 


$318,938 


$318,938 


$318,938 


$246,447 


$318,938 


$394,431 


1 u irvL 

$ 2,554,506 


8 


19.505 


19.904 


23,789 


22,027 


22,169 


15,114 


6,071 


48,493 


177.072 


C 


43.269 


17.605 


27.562 


23.656 


23,569 


34,842 


12,210 


33,5tO 


216,223 


D 


51.317 


59.539 


42,087 


52,227 





35,793 


36,032 


49,498 


326,493 


E 


184.378 


196.169 


179.122 


209,562 


207.747 


241 ,655 


145.013 


323.482 


1.687,128 


F 


154.385 


194.588 


179.128 


207.316 


207,338 


136,854 


145,018 


208,484 


1.433.1 11 


G 


56,680 


71.441 


65.764 


76,112 


76,121 


57,924 


53.240 


83.862 


541,144 


H 


162.005 


167.511 


179.045 


177.781 


178,451 


221 .809 


124.353 


278,347 


1.489,302 


1 





























J 














76,099 











76,099 


K 





























L 





























M 


43.708 


45,924 


74,325 


71.183 


68,711 


100,238 


49,849 


125.576 


579.514 


N 


393,228 


393.228 


393.228 


393.228 





424,650 





429,650 


2,427,212 
































P 





























(i 





























R 


8.930 


95,372 


9.462 





50,759 


153.018 





466.067 


783 ,608 


S 


3,431 


9.748 





8.695 





22,634 


14,002 


122,253 


180,763 


T 


33,599 


108.361 


56,780 


109.950 


64,298 


77.799 


85,819 


72,282 


608,888 


U 





























V 


96,265 


96.265 


96,265 


96,265 


96,265 


68,902 


96,266 


63,614 


710.107 


w 


105,286 


105,286 


105,286 


105,286 


100,000 


100,000 


100,000 


36,130 


75 7. 2 74 


X 








2,119 











14,428 


59,000 


75,547 


Y 


503,956 


505,686 


481 ,677 


504,198 


472,748 


504,199 


472,748 


983.908 


4,429,120 


z 


326,193 


372.632 


326,193 


372,632 


360,563 


331,696 


372,632 


531,401 


2,993,942 



TOTAL $2,505,073 $2,778,197 $2,560,770 $2,749,056 $2,323,776 $2,773,574 $2,o46,6l9 $4,309,988 $22,047,053 



ORIGINAL FAQE 13' 
OF POOR QUALITY 



278 



TABLE LXV(c) - PHASE VI OBLIGATIONS OF FUNDS BY VEHICLE 
POD REIMBURSABLES 







NAVY 




A.F. 


TOTAL 


NASA £• DOD 


TASK 


178 


182 


192 


SUBTOTAL 
524,198 


179 


VI TOTAL 


A 


$ 205,260 $ 


318,938 $ 


$ 


$ (1) 


$ 524,198 


$ 3.078,704 


B 


7,075 


10,591 


5,160 


22.826 


16.743 


39,569 


216,641 


C 


37,675 


32,292 


35.529 


105,496 


25,673 


131,169 


347.392 


D 


32,591 


41 .959 


Phase VI 1 


74.550 


(2) 


74.550 


401 .043 


E 


211,315 


2,255 


9.831 


223,401 


52,483 


275,884 


1.963.012 


F 


119,517 








119,517 





119.517 


1.552,628 


G 


58,863 








58,863 





58.863 


600.007 


H 


149,689 


150.371 


240.536 


540.596 


324.708 


865,304 


2,354,606 


1 























J 




















76,099 


K 























L 























M 


42.508 


42,508 


66,379 


151,395 


99.221 


250,616 


830.130 


N 


393,228 


393.228 


Phase VI 1 


786.456 


220.364 


1,006.820 


3.434.032 


























P 























Q 




















00 


R 


26.226 


53,080 


193,519 


272.825 


212.628 


485.453 


1 .269,061 


S 




















180,763 


T 


27.817 


27.818 


79,387 


135.022 


27.817 


162,839 


771,727 


U 























V 


31.003 


96.265 


31 .004 


158,272 


99,505 


257,777 


967,884 


w 


105,286 


105,286 


100.000 


310.572 


100,000 


410,572 


1,167.846 


X 








Phase VII 











75,547 


Y 


488.535 


527.181 


542.326 


1.558,042 


510.984 


2.069.026 


6.498.146 


z 


354,136 
$2.2qo.724 $ 


368,559 
2.170.331 $ 


667,459 
1.971,130 


1.390.154 
$6,432,185 


331,036 


1,721 ,190 


4.715.132 


TOTALS 


$2,021,162 


$8,453,347 


$30,5eo*4oe 



(1) Included in Navy annual costs. 

(2) Included in Task R. 



ORIGINAL PAGE IS 
279 ^^ POOR QUALITY 



TABLE LXVI - PHASE VI HARDWARE OBLIGATIONS 
(Does not include mission peculiars - for comparison) 



CONTRACT 
TASK 


H 


M 


T 


V 


Y 


Z 


TOTAL 


VEHICLE 
NO. 


1it9.689 < 


! 4o ,000 


$ 26,161 < 


i 31,003 


$ 508,947 


$ 358,300 




178 $ 


$ 1,114,100 


179 


3^+1,732 


50,529 


26,161 


99,505 


504,304 


362 ,934 


1.385,165 


180 


162,005 


41 ,208 


3,427 


96,265 


532 ,472 


330,357 


1.165.734 


181 


262,991 


43,416 


33,705 


96,265 


519,458 


405,164 


1,360.909 


182 


167,126 


40,000 


26,161 


96,265 


527.I8I 


372,724 


1.229.457 


183 


179,045 


71.817 


26,608 


96,265 


510,193 


330,357 


1.214.285 


184 


177,781 


68,675 


35,294 


96,265 


548,830 


405,164 


1,332,009 


185 


183,254 


64,286 


34,858 


52,804 


546,759 


387,048 


1 ,269,009 


186 


276,687 


76,467 


26,161 


86,088 


56t ,676 


400,758 


1,427.837 


187 


178,451 


66,403 


27.381 


96,265 


508,009 


364,727 


1.241,236 


188 


229.824 


77,544 


38,216 


62,804 


541,379 


402,074 


1,351,841 


189 


232,588 


97,930 


27.738 


68,902 


552,603 


335,661 


1,315,^22 


190 


124,353 


'»7,3't1 


27,450 


96,266 


517,380 


376,797 


1,189,587 


191 


278,347 


119,868 


26,160 


63,614 


556,101 


383,909 


1 ,427,999 


192 


240,536 


63,87.1 


79,387 


31 ,004 


5^2,326 


669,967 


1,627,091 


S-M 


702,142 


302.651 





331,390 


77,920 


655,861 


2,069,964 


S-0 





3,200 


44,665 


3,575 


212,566 


359.378(3) 


623,384 



TOTAL $3,886,551 $1,275,206 $509,533 $1,504,545 $8,268,104 $6,901,180 $22,345,119 



S-M Sustaining Major Contracts. 

S-0 Sustaining Others. 

(a) NASA-$266,215, D0D-$93,163. 



ORIGINAL PAGE IS 
OF POOR QUALITY 

280 

TABLE LXVII - SUMMARY OF PHASE VI OBLIGATIONS BY TASK (490) 

TASK NASA (VEH.) NASA (SUST.) FOREIGN _DOD (VEH.) POD (SUST. ) TOTAL 

A $ 2,554,506 $ 661,141 $ 1,279,709 

B 177,072 139,527 69,375 

C 216,223 22,099 64,793 

D 326,493 24,875 165,248 

E 1,687,128 1,910,948 861,832 

F 1.433.111 648,885 651,669 

G 541.144 276.361 246,822 

H 1.489.302 702,142 838,010 

I 834,852 2,502.726 

J 76.099 59.529 728,324 

K 15,948 

L 407,519 

M 579,514 305,851 265.638 

N 2,427,212 1,242,528 

88,280 118,500 

P 318,272 

Q 9,277 434,120 

R 783.608 5.321.496 133.174 

S 180,763 320,628 2,398 

T 608,888 44,665 126.685 

U 2,359,767 270,420 

V 710,107 334.965 297.962 
W 757,274 4,114 405,286 
^ 75.547 153,043 74,409 

Y 4,429.120 290.486 2,189,364 



Z 



TOTAL 



2,993,942 922,076 1,566,676 



$ 524,198 


$ 


$ 5,019.554 


39,569 





425,543 


131,169 





434,284 


74,550 





591,166 


275,884 


5,245 


4,741 ,037 


119.517 





2,853,182 


58.863 





1,123,190 


865,304 





3,894,758 





569.146 


3.906,724 








863 ,952 








15,948 








407.519 


250,616 





1,401 ,619 


1 .006.820 





4,676.560 





73,411 


280.191 








318,272 








443.397 


485.453 


876,434 


7,600.*&5 








503,789 


162.839 





943,077 





591 .026 


3,221,213 


257.777 





1 .600,811 


410.572 





1.577.246 





8,309 


311.308 


2.069.026 





8,977.996 


1.721.190 


93.163 


7.297.047 


$8,453,347 


$2,216,734 


$63,429,548 



OR'GINAL PAQ- r 
OF POOR QUALITY 



m 



281 
TABLE LXVIll(a) - VEHICLE S-I78 OBLIGATIONS (MAJOR CONTRACTS) BY TASKS 



TASK 


(1)NAS1-5610 
(2)nAS1-6020 

$ 


NASI -71 99 
$ 


(3^NASl-58a3 
NASl-7256 

$205,260 


NASI -10000 
$ 


(4) NASI 
NASI 

$ 


-11000 
-12500 


TOTAL 


A 


$ 205,260 


B 








7,075 






7,075 


C 






3,059 


34,616 






37,675 


D 












32,591 


32,591 


E 


i2)70,]kk 




140,039 


1,132 






211.315 


F 






119,517 








119,517 


G 






58,863 








58.863 


H 
J 
K 

L 
M 






149,689 








149.689 








42,508 






42,508 


N 
P 
R 
S 
T 








393,228 






393,228 








20,412 




5,814 


26,226 






26,161 


1.656 






27,817 


V 






31,003 








31,003 


W 
X 
Y 








105,286 






105.286 


(1) 16,500 


i+71.835 








(4)200 


488,535 


Z 


(1) 888 
$ 87.532 


293,123 


(3)60,125 
$793,716 








354,136 


TOTAL 


$76it,958 


$605,913 


$ 


38.605 


$2,290,724 



282 



ORIGSNAL PAGE IS 
OF POOR QUALITY 



TABLE LXVIIl(b) - VEHICLE S-1 79 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 

NASl-IIOOOAJJj 
TASK NAS1-7199A NAS1-7256NA NAS1-10000NA NASl-1 I^OOa '' ^ NAS1-12500NA TOTAL 



A 

B 

C 

D 

E 

F 

G 

H 

J 

K 

L 

M 

N 

P 

R 

S 

T 

V 

W 

Y 

Z 



$ $ $ 

l6,7it3A 16, 7^*3 

25.673N 25.673 

4,1 73N ii8,310A 52.483 



56,86itN 148,375A 119,469A 324,708 





48, 692 N 


50,529A 
9.258a 








220,364a 
203,370NA 


99,221 
220,364 

212,628 




26,161A 


1,656a 










27,817 




31 ,003A 


68,502A 








100,000A 


99.505 
100,000 


470,784 






40 


200 


(1) 




510,984 


218,935 






112 


.101 


(2) 




331,036 



TOTAL $689,719A $162,720NA $308,166NA $152,301A $708,256NA $2,021,162 



A - Air Force 
N - Navy 



TASK 
A 
B 
C 

D 

E 

F 

G 

H 

J 

K 

L 

M 

N 

P 

R 

S 

T 

V 

W 

X 



TOTAL 



283 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLE LXVIII(c) - VEHICLE S-I80 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 
NASI -6020 NASI- 7199 NASI -7256 



(1)NAS1-5610 
NASI -10000 (2)NAS1-6935 



$ 



$ 



2,602 



495,026 
293,123 



$ 



10, it 79 



29,619 



2,616 
31,003 



$ 318,938 $ 

6,424 

43,269 

51,317 

184,378 

154,385 

56,680 

132,386 



TOTAL 



$ 



318,938 
19,505 
43,269 
51,317 

184,378 

154,385 
56,680 

162,005 



43 ,708 




'•3 ,708 


393,228 




393,228 




(2) 8.930 


8,930 


3,431 




3,431 


30,983 




33,599 


65,262 




96,265 


105,286 




105,286 




(2) 8,930 


503.956 




(1) 33.070 


326,193 



$ 2,602 $ 788,149 $73,717 $1,589,675 $ 50,930 $2,505, 



073 



TABLE LXVIIl(d) - VEHICLE S-I8I OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 



TASK 


NASI 
$ 


-7199 


NAS 
$ 


1-7256 


NASI 
$ 


-9258 


NASI -10000 
$ 318,938 


NASI -6935 
$ 


TOTAL 


A 


$ 318,938 


B 






10 


,479 








9.425 




19,904 


C 
















17,605 




17,605 


D 
















59.539 




59,539 


E 
















196,169 




196.169 


F 
















194,588 




194,588 


G 
















71 ,441 




71 .441 


H 
J 
K 
















166,860 


651 


167.511 


L 
M 
















45,924 




45 .924 


N 
p 
















393.228 




393.228 


R 
















95,372 




95.372 


S 






7, 


180 








2.568 




9.748 


T 






26, 


161 








82,200 




108,361 


V 






31, 


003 








65,262 




96,265 


W 

Y 
















105,286 




105,286 


A 

Y 


472 


,747 














32,939 


505.686 


Z 


245,840 






126 


,792 








372,632 


TOTAL 


$718,; 


587 


$74,823 


$126, 


792 


$1 


,824,405 


$33,590 


$2,778,197 



NASI -10000 


NASI 
$ 


-6935 


TOTAL 


$ 318,938 


$ 318,938 


7,588 






10,591 


32,292 






32,292 


41,959 






41 ,959 


2,255 






2,255 



ORlGUvSAL PACSfe SS 
OF POOR QUALITY 

285 

TABLE LXVIII(e) - VEHICLE S-182 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 

(l)NASI-IIOOO 
TASK NASI -6020 NASI -71 99 (2) nas1-7256 

A $ $ $ 

B 3,003 

C 

D 

E 

F 

G 

" 150,371 150,371 

J 

K 

L 

^ 42,508 42.508 

^ 393,228 393,228 

P 

^ 53,080 53,080 

S 

T 

V 

w 

X 
Y 
Z 

TOTAL $3 003 





(2) 26,161 


1,657 




27,818 




(2) 31,003 


65,262 
105,286 




96,265 
105,286 


488,850 


(1)200 




38,131 


527,181 


368,559 








368,559 


857.409 


$57,364 


$1,214,424 


$38,131 


$2,170,331 



OF POOR QUAurv 
286 

TABLE LXVIII(f) - VEHICLE S-I83 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 
TASK NASI -5610 

A 

B 

C 

D 

E 

F 
G 
H 
J 
K 
L 
M 
N 
P 



NASI -71 99 


NASI -7256 
$ 


NASI -10000 
$ 318,938 


NASI 


-6935 


TOTAL 


$ 


$ 318,938 




20,960 


2,829 

27,562 

42,087 

179,122 

179,128 

65,764 






23,789 
27,562 
42,087 
179,122 
179,128 
65,764 






153,604 


25,441 


179,045 



74,325 74^325 

393,228 393,228 



R 
S 

''" 26,161 30,619 



532 8,930 9^i,62 



^ 31,003 65,262 

W 

X 

Y 472,747 

z 33.070 293,123 



56,780 

96,265 
105,286 105,286 

2,119 2,119 

8,930 481,677 

326,193 



TOTAL $33,070 $765,870 $78,124 $1,638,286 $45,420 



$2,560,770 



OF POOR QUALITY 



287 



TABLE 
TASK 
A 
B 
C 
D 
E 
F 
G 
H 
J 
K 
L 
M 
N 
P 
R 
S 
T 
V 
W 
Y 



LXVIlKg) - VEHICLE S-184 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 
NASI -71 99 NASI -7256 NASI -9258 

^ $ $ 



245,840 



2,427 
26,161 
31,003 



126,792 



NASI -10000 


NASI- 
$ 


-6935 


TOTAL 


$ 318,938 


$ 318,938 


22,027 






22,027 


23.656 






23,656 


51,211 






52,227 


109.561 






209,562 


207,316 






207,316 


76,112 






76,112 


177,781 






177,781 



71,183 

393,228 



6,268 
83.789 
65,262 
105,286 



31.451 



71,183 
393,228 



TOTAL $718,587 $59,591 $126,792 $1,812,635 $31,451 



8,695 
109,950 
96,265 
105,286 
504,198 
372,632 

$2,749,056 



$ 318.938 


^5 


612 


16 


066 


45 


309 


151 


,969 


184,566 


67 


.762 


183 


,254 



•j:v. r.-'--^ "^•"^ 
288 

TABLE LXVI 11(h) - VEHICLE S-I85 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 
TASK NASI-56IO NASI -71 99 NASI -7256 NASI -9258 NASI -10000 NASI -6935 TOTAL 

A $ $ $ $ $ 318,938 $ 

B 13,973 31,639 

C 16,066 

D 45,309 

E 151,969 

F 184,566 

G 67,762 

H 183,254 

J 
K 
L 
M 
N 
P 
R 
S 
T 
V 
W 
X 
Y 
Z 

TOTAL 













66,794 






66,794 












393.228 


8,930 




393,228 
8,930 






14,360 












14,360 






26,161 






83,352 






109,513 






31 ,003 






21 ,801 
105,286 






52,804 
105,286 




470,784 










31,451 




502,235 


33,695 


170,403 




126 


792 








330,890 


$33,695 


$641 ,187 


$85,497 


S126 


792 


$1 ,669 564 


$40,381 


$2 


,597,516 



OF POOR QUALITY 



289 



TABLE LXVIil(i) - VEHICLE S-186 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 



TASK 


NASI 
$ 


-7199 


NASI -7256 
$ 


NASI 
$ 


-9258 


NASI -10000 
$ 159,488 


NASI -12500 
$ 151,412 


NASI -6935 
$ 


TOTAL 


A 


$ 310,900 


B 














^.474 






4,474 


C 














Tt,495 






14,495 


D 














43,086 






43,086 


E 












60,339 


126,138 






186,477 


F 












72,718 


82.919 






155,637 


G 












26,696 


35.161 






61,857 


H 
J 












129,973 


135,284 




651 


265,908 


K 






















L 






















M 












58,345 


20,430 






78,775 


N 
P 














424,650 






424,650 


R 












1.358 








1,358 


S 






7,180 






10,779 








17,959 


T 






26,161 






46,284 








72,445 


V 






31,003 






31 ,801 


23.284 






86,088 


W 
X 














100,000 






100,000 


Y 


^+70, 


784 


15.554" 










30, 


,710 


517,048 


z 


ZifS.B^tO 




126, 


792 










372,632 



TOTAL $716,624 $79,398 $126,792 $597,781 $1,161,333 $31,361 



$2,713,789 



'-Contract NASI -6020. 



TASK 






290 ^'^'pOO^ 



TABLE LXVIII(j) - VEHICLE S-I87 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 



A 


$ 


. - - - ■ , — ^ V 

$ 


$ 318,938 


$ 


i 1 IHUV 


NASI -12500 
$ 


NAS1-6935 
$ 


TOTAL 
$ 318,938 


6 






17,865 






4.304 






22,169 


C 






3,114 






20.455 






23,569 


D 




















E 






207,331 






416 






207,747 


F 






207.338 












207,338 


G 






76,121 












76,121 


H 






177.800 










651 


178,451 


J 












76,099 






76,099 


K 




















L 




















M 






68,711 












68,711 


N 




















P 




















R 






1 . 786 






48.973 






50,759 


S 




















T 




26.160 


38.138 












64,298 


V 




31.003 


65.262 












96.265 


W 












100,000 






100,000 


X 




















Y 


472,748 
















472.748 


Z 


293,123 






34 


501 




32 


939 


360, ■:C3 



TOTAL 



$765,871 $57,163 $1,,82.4o4 S34.50I $250,247 $33,590 $2,323,776 



291 



TABLE LXV,M(.) - VEHICLE S-,88 OBLIGATIONS OP MAJOR CONTKACTS BV TASKS 
lASK MSW13S MSWZ56 ,,si^ ^..^^^ ^^^^^^ ^^^^^ ,,,,, 

$ 239.272 $91,671 $ $ 330.943 



'^ $ $ $ 

B 

C 

D 

E 

F 

G 

H 

J 

K 

L 
M 
N 
P 
R 

^ 21,540 

^ 26,160 



V 

w 

X 

Y 470,784 

Z 245,840 



126,792 



12,324 894 



5,088 
1 1 . 760 
29.828 
31.003 31,801 



TOTAL $716,624 $78,703 $,26,792 $ 824,805 $927,341 



13,218 



3.259 18,763 22.022 

40,821 40.821 

137.010 76,115 213,125 

116,243 50.205 166,448 

^2,675 21.288 63.963 

136.472 81,923 65O 219.045 



59.073 21,011 80,084 

^24.650 424,650 



5,088 

33,300 

55,988 

62,804 

100,000 100,000 

32.939 503,723 

372.632 



$33,589 $2,707,854 



292 OF PCOK QUALrnf 



TABLE LXVIlUl) - VEHICLE S-I89 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 
TASK NASI -6933 NASI -7199 NASI -7256 NASI -9258 NAS1-10000 NAS1-11400 NASI -12500 TOTAL 

A $ $ $ $ $ $ 

B 8,123 

C 

D 

E 1 ,889 

F 1,890 

G 694 

H 1,618 

J 

K 

L 

M 651 

N 

P 

R 

S 10,779 



T 26,160 50,061 

V 31,003 

W 
X 

Y 3 1,^+51 472,7^8 

z 170,403 126.792 34,501 



$ 246,447 


$ 246,447 


6,991 


15.114 


34,842 


34.842 


35,793 


35,793 


239,766 


241,655 


134,964 


1?'i,854 


57,230 


57,924 


220,191 


221 ,809 



99,587 


100,238 


424,650 


424,650 


153,018 


153,018 


11,855 


22,634 


1,578 


77,799 


37,899 


68,902 


100,000 


ICO, 000 




504,199 




331,696 



TOTAL 531,451 $643,151 $57,163 $126,792 $75,705 $34,501 $1,804,811 $2,773,574 



TOTAL 



ORiGl?^-^-'^ PASS IS 
OF POOR QUALITY 
293 

TABLE LXVIIl(m) - VEHICLE S-190 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 



TASK 


NASI -71 99 
$ 


NASI -7256 
$ 


NASI -9258 
$ 


NASI -10000 
$ 318.938 


NAS1-12500 
$ 


TOTAL 


A 


$ 318,938 


B 








^,097 


1.974 


6.071 


C 








3,221 


8.989 


12,210 


D 










36,032 


36,032 


E 








1^5.013 




145.013 


F 








145,018 




145,018 


G 








53,240 




53,240 


H 








124,353 




124,353 


J 








429,726 


291,171 


720 ,897^ 


K 














L 














M 

H 








49,849 




49,849 


R 
S 




2,39B 




1 1 ,604 




14,002 


T 




26, 160 




59,659 




85.819 


V 




31.00i* 




65,262 




96,266 


X 










100,000 


100,000 


Y 


^72 , 7k8 










472,748 


Z 


24ii,840 




126,792 






372,632 




$718,588 


$59,562 


$126,792 


$1,409,980 


$438,166 


$2,753,088 



(1) San Mai CO re imbursab ie funds. 



A 

B 

C 

D 

E 

F 

G 

H 

J 

K 

L 

M 

N 

P 

R 

S 

T 

V 

W 

X 

Y 

Z 



ORIGINAL PAQE IS 
OF POOR QUALITY 

29^ 
TABLE LXVIIl(n) - VEHICLE S-191 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 



NASI -1702']^ 
NASI -6935 NASI -71 99 NASI -7256" NASI 

$ $ $ $ 


-92^8 


NASI -10000 


NASI 
NASI 


-lOSOO*^^ 

-11400'^ NASI -12500 


TOTAL 




$159,it88 


$ 


$ 


234,943 


$ 394,431 






32,206 






16,287 
33,510 
49.498 


48.493 
33.510 
49,498 






128,it05 






195.077 


323.482 






79,818 






128.666 


208,484 






29.304 






5'' ^5Q 


83,862 






68.414 






209,933 


278,347 







3.200-'" 






27,436 






94,940 


125,576 






5,000""''' 












424,650 


429,650 


5,780 




298,325"''''' 

2,834 "■■•■ 

26,160 '■ 

31 ,004'' 






161,962 

46,122 
32,610 






119.419 

36.130 
59,000 


466,067 
122,253 
72,282 
63.614 
36,130 
59.000 


37.231 


472,748 


72,000''"' 








401 


.929^'^ 




983.908 




171,652 


150.000"'"'' 


126 


792 




82 


.957'^ 




531 ,401 



TOTAL $43,011 $644,400 $588,523 $126,792 $765,765 $484,886 $1,656,611 $4,309,988 



ORIGINAL PAGE IS 
OF POOR QUALITY 



295 



TABLE LXVIIl(o) - VEHICLE S-192 OBLIGATIONS OF MAJOR CONTRACTS BY TASKS 
TASK NAS1-7199 NASI -72 56 NASI -11400 NAS1-12500 NAS1-13100 NASI -1^200 NAS1-15000 NAS1-15100i TOTAL 



A $ 


5 


% 


$ 


$ 




$ 




$ 


$ 


$ 


B 






921 










4,239 




5,160 


C 






11,203 










24,326 




35.529 


£ 






9.831 














9,831 


F 






















G 






















H 






166,616 










73,920 




240,536 


J 






















K 






















L 






















M 






13,871 










50,968 


1,540 


66,379 


N 






















P 






















R 






101,670 










113,506 




215,176 


S 






















T 


26,160 














53,227 




79,387 


U 


31 ,00k 


















31 ,004 


W 
X 
















100,000 




100,000 


Y k-n ,835 
















70,49! 




542,326 


z 




132,903 




286. 


147 


248 


,40P 






667,459 



TOTAL $471,835 $57,164 $132,903 $304,112 $286,147 $248,409 $490,677 $1,540 $1,992,787 

(1) Complete costs of vehicle S-192 inciude launching and shipping costs and data analysis 
in Phase \,' I I are not included above. 



ORIGINAL PAGE IB 
296 OF POOR QUALITY 



TABLE LXIX - PHASE VI SUSTAINING EFFORT BY MAJOR CONTRACTS 



TASK 


(1)NAS1-6020 
NAS1-6935(2)NAS1-7199 

$ $ 


NASI -7256 

$ 


NASI -9258 
$ 


NASI -10000^^^ NASI -12500 
$ 318,938 $ 342,203 


NAS 
$ 


-15000 


TOTAL 


A 


$ 661,141 


B 
















139,527 








139,527 


C 
















22,099 








22,099 


D 
















24,875 








24,875 


E 




10,it90 


36,220(1) 










1,580,104^2) 


284,134 






1,910,948 


F 
















461 ,478 


187,407 






648,885 


G 




13,600 












183,297 


79,465 






276.362 


h(6) 




549,619 


53,002^'^ 


74,600 










19,679 


5 


242 


702,142 


J 


















476,373^'*^ 






476,373 


K 
















15,948 








15,948 


L 
















407,519 








407,519 


„(6) 

M 




77,787 


87.549^^) 












137.315 






302.651 


p 
















287,272 








287,272 


R 


1 


.607.562(5) 




2 


,489,280 


720, 146^^) 


98,057 






4,915,045 


S 






81 .504^^) 


106,839 








230,580 








418,923 


t(6) 


























v(6) 
W 












170 


000 


65,262 


52,625 


43 


503 


331.390 


X 
y(6) 






77,920(2) 


















77,920 


z(6) 




483,389 


172, 472^^^ 


















655,861 


TOTAL 


$2 


,742,447 


$508,667 


$181,439 


$2 


,659 


280 


$4,457,045 $1 


,677,258 


$48 


745 


$12,274,881 



(1) Includes canceled CAS-B. 

(2) Includes $5,245 (NAVY). 

(3) Includes $43,577 (NAVY). 

(4) Includes Kalian Funds. 

(5) Includes PAET $200,000 for heal shield deve lopiiionl. . 

(6) Table LXV I includes hardware obligations. 



29? 



TAfeLf LXX - SCOUT PROGRAM FY 1972 OBLIGATIONS, 
October ] , 1979 

FISCAL YEAR FUNDS FY 1971 & PRIOR FY 1972 

DEVELOPMENT (890) 



FY 1959 


(STG) 


FY 1959 




FY I960 




FY 1961 




FY 1962 




FY 1963 




FY 1961 


(STO) 


FY 1962 


(STO) 


FY 1963 


(STO) 


SUBTOTAL 




PRODUCTION 


(^♦90) 


FY 1961 




FY 1962 




FY 1963 




FY 196it 




FY 1965 




FY 1966 




FY 1967 




FY 1968 




FY 1969 




#FY 1970 




FY 1971 




FY 1972 




FY 1965-72 (STO) 


SUBTOTAL 




SEAM (A97) 




FY 1964 




FY 1965 




FY 1966 




FY 1967 




FY 1968 




FY 1968 


(STO) 


SUBTOTAL 





TOTAL 



$ 3,810.488.00 $ 3.810.488.00 

3,366,000.00 $ -406.75 3,365,593 25 

2 978.043.04 2.978.043.04 

6.600,000.00 6.600.000.00 

2.?i;.217.A2 2.9n.217.'»2 

3,^84.149.22 3,484,149.22 

300,000.00 300,000.00 

1,725,000.00 1,725.000.00 

402,000.00 402,000.00 

$25,5 76,897.68 $ -406.75 $25,576,490.93 



$ 1,200,000.00 $ 1,200,000.00 

6.582,817.92 6.582.817.92 

8,054,000.00 8,054,000.00 

8,100,000.00 8,100,000.00 

5,688,300.00 5,688,300.00 

7,600,000.00 7,600,000.00 

5.399,602.00 5.399,602.00 

5. 163.000.00 5,163,000.00 

12,491,000.00 $ -12.00 12,490,988.00 

13,035,00.00 -202.25 13,034,797.75 

12,517,201.54 21,720.60 12,538,922.14 

14,262,726.50 14,262,726.50 

1,688,700.00 756.000.00 2,424.700.00 

$87,499,621.46 $15,040,232.85 $102,539,854.31 



$ 3.400,000.00 $ 3,400,000.00 

7,494.526.42 7,494.526.42 

3,999.954.00 3,999.954.00 

3.985,091.00 3.985,091.00 

4,962.661.35 4,962,661.35 

36.000-00 36,000.00 

$ 23,678,232.77 s 23.878,232.77 



# Includes San Marco. 



ORiGlf^AL PAGE \S 
OF POOR QUALITY 



298 



TABLE LXX Continued - SCOUT PROGRAM FY 1972 OBLIGATIONS, 



FISCAL YEAR FUNDS 



October 1 , 1 979 
FY 1971 6 PRIOR 



FY 1972 



TOTAL 



SAN MARCO 

FY 1963 

FY 196't 

FY 1965 

FY 1966 

FY 1967 

FY 1968 

FY 1964 Trust Fund 

FY 1965 Trust Fund 

FY 1967 Trust Fund 

FY 1969 Trust Fund 

FY 1970 Trust Fund 

SUBTOTAL 

ESRO IB 

FY 1970 
FY 1971 

SUBTOTAL 

ESRO \\l 

FY 1970 
FY 1971 

SUBTOTAL 
UK 

FY 1972 

SUBTOTAL 

DELTA MOTORS 

FY 1964 
FY 1965 
FY 1966 

SUBTOTAL 



1,870,190.62 

337,733-13 

500,000.00 

350,000.00 

100,000.00 

70,000.00 

200,000.00 

480,465.00 

29,672.84 

42,529.97 

123,495.95 



$ -4.274.90 



-1,548.00 

5,479.09 
125,781.60 



$ 1,865,917.72 

337,733.13 

500,000.00 

350,000.00 

100,000.00 

70,000.00 

200,000.00 

478,917-00 

29,672.84 

48,009.06 

249.277-55 



$ 4,104,087-51 $ 125.437-79 $ 4,229,525.30 



$ 1,861,910.00 
347,571-87 



$ 2,209,481.87 $ 



886.51 
34,991.06 



35,877.57 $ 



$ 430,000.00 
548,758.00 
488,157.00 

$ 1.466.917.00 



C ONSTRUCTION OF FACILITIES (NAS A) 



FY i960 (STO) 
FY 1962 

SUBlOTAL 



>'---NASA TOTAL 



$ 1,200,000.00 
1,433,131.43 

$ 2,633.131.43 



-0.41 



$ 1.861. 909. 59 
347,571-87 



-0.41 $ 2,209,481.46 



3,204.87 $ 
18,096.57 _ 



4,091.38 
53,087-63 



21,301.44 $ 



,350.96 $ 



57,179.01 



1.350-96 



,350.96 $ 



1,350.96 



$ 430.000.00 
548,758.00 
488,157-00 

$ 1,466,915-00 



$ 1,200,000.00 
1.433,131.43 

$ 2,633,131.43 



$147,404,245.29 $15,187,915-88 $162,592,161-17 



■•'•--.■Does' not include subat lotments received nor SRT funds. 



OF POOR QUALITY 



299 



TABLE LXX Concluded - SCOUT PROGRAM FY 1972 OBLIGATIONS 



FISCAL YEAR FUNDS 



October I , 19 B 
FY 1971 & PRIOR FY 1972 



TOTAL 



AIR FORCE 














'■^FY I960 


$ 


5,603,061.78 


$ 


-2.908.00 


$ 


5,600,153.78 


'•^FY 19o} 




l,I15,87it.28 








1,115,874.28 


FY 1962 




10,273.856.95 








10,273,856.95 


FY 1963 




6,932,001.20 








6,932,001.20 


FY 196^1 




977,381.00 




-13,754.00 




963,627.00 


FY 1965 




2,7^*5,320.44 




-3,182.00 




2,742,138.44 


FY 1966 




2,025,848.58 








2,025,848.58 


FY 1967 




9.009,953.83 




2,581,589.74 




11,591,543.57 


FY 1968 




2,128,252.84 




755,657.91 




2,883,910.75 


FY 1967-8-9-0 (VAFB) 




679.281.00 








679.281.00 


FY 1969 




484,533-71 








484,533.71 


FY 1971 




4,345.24 




19,371-61 





23,716.85 


SUBTOTAL 


$ 


41,979,710.85 


$ 


3,336,775-26 


$ 


45,316,486.11 


NAVY 














FY 1961 


$ 


1 ,800.000.00 






$ 


1,800,000.00 


FY 1962 




7,899,999.12 








7,899,999.12 


FY 1965 




3,348.00 








3,348.00 


FY 1971 






$ 

$ 


2,600.00 
2.600.00 


$ 


2,600.00 


SUBTOTAL 


$ 


9,703,347.12 


9,705,947.12 


AEC 














FY 1963 (Al) 


$ 


26,563.60 






$ 


26,563-60 


FY 1963 




2,371 ,000.00 









2,371,000.00 


SUBTOTAL 


$ 


2,379,563.60 






$ 


2,397,563.60 


REIMBURSABLE TOTALS 


5 


54,080,621 .57 


$ 


3,339,375.26 


$ 


57,419,996.83 



TOTAL 



$201,484,866.86 $18,527,291.14 $220,012,158-00 



■''6O9A Program. 



300 



TABLE LXXI - SCOUT PROGRAM FY 1973 OBLIGATIONS. 
October 1 , 1979 

FISCAL YEAR FUNDS FY 1972 & PRIOR FY 1973 

DEVELOPMENT (890) 



FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 



1959 
1959 
i960 

1961 
1962 
1963 
1961 
1962 
1963 



(STG) 



(STO) 
(STO) 
(STO) 



SUBTOTAL 



PRODUCTION (490) 

FY 1961 

FY 1962 

FY 1963 

FY 196^4 

FY 1965 

FY 1966 

FY 1967 

FY 1968 

FY 1969 

^FY 1970 

FY 1971 

FY 1972 

FY 1973 

FY 1965-73 (STO) 

SUBTOTAL 

SEAM (^97) 



FY 
FY 
FY 
FY 
FY 
FY 



1964 
1965 
1966 

1967 
1968 
1968 



(STO) 



$ 3,810,488.00 

3,365,593.25 
2,978,043.04 
6,600,000.00 
2,91 1,217.42 
3,484,149.22 

300,000.00 
1,725,000.00 

402.000.00 

$ 25,576,490,93 



$ 1,200, 
6,582, 
8,054, 
8,100, 
5,688, 
7,600, 

5,399, 
5,163, 
12,490, 
13,034, 
12,538, 
14,262, 



000.00 
817.92 
000.00 
000.00 
300.00 
000.00 
602.00 
000.00 
988.00 

797.75 
922.14 
726.50 



2.424.700.00 



-126.76 

2,077.86 

81,273.50 

8,665,341.26 

129.000.00 



TOTAL 



$ 3,810,488,00 
3,365,593.25 
2,978,043.04 
6,600,000.00 
2,911,217.42 
3,484,149.22 
300,000.00 
1,725,000.00 
402.000.00 

$ 25,576,490.93 



$ 1 



,200, 
6,582, 
8,054, 
8,100, 
5,688, 
7,600, 

5,399, 

5,163, 
12,490, 
13,034, 
12,541, 
14,344, 

8,665. 

2 , 553 , 



000.00 

817.92 

000.00 
000.00 

300.00 

000.00 

602.00 

000.00 

988,00 
620.99 

000.00 
000.00 
341.26 
700.00 



$102,539,854,31 $ 8,877,565.86 $111,417,420.17 



SUBTOTAL 



$ 3.400,000.00 
7,494,526,42 
3,999,954,00 
3.985,091,00 

4,962,661,35 
36.000.00 

$ 23,878,232,77 



$ 3,400,000,00 
7,494,526,42 
3,999.954.00 
3,985,091.00 

4,962,661.35 
36.000,00 

$ 23,878,232,77 



i> Includes San Marco , 



301 

TABLE LXXI Continued - SCOUT PROGRAM FY 1973 OBLIGATIONS. 

October 1, I979 

FISCAL YEAR FUNDS FY 1972 & PRIOR FY 1973 TOTAL 

SAN MARCO 

n\tl ' '■^'■nl-n- ' 1,865,9,5.72 

J \^l 500.000.00 lll:lll:ll 

FY ^7 ?^nS'°°°-°° 350 000.00 

p! l^Jl 100.000.00 100.000.00 

'^^ 70.000.00 70 000 nn 

FY ,96^ Trust Fund 200.000.00 ^oSiZ' 

FY 1965 Trust Fund it78.917.00 478 917 00 

FY 1967 Trust Fund 29.672.8/f 29 6)2'82 

FY 1969 Trust Fund 48,009.06 48 009 06 

FY 1^75 t'%' p"1 249,277.55 $ -6.Ol8.63 24;:258:92 

FY 1973 Trust Fund ^78.6Q';.04 478:6q-^.04 

^^^™^'^'- $ ^.229.525.30 $ 472.676.41 $ 4.702.201.71 
ESRO IB 

II ]ll°, $ '•?f!'509.59 $ -273.64 $ 1.861,635.95 

350.000.00 



■"^ '971 347.571.87 2.428.n 



SUBTOTAL 
ESRO IV 



$ 2,209,481.46 $ 2.154.49 $ 2,211,635.95 



tl 111° ^ ^.091.38 $ 45,888.67 $ 49,980.05 

ly.lll 53.087.63 1,446.912.37 1.500.000.00 

ll llii 800.000.00 800.000.00 

^^ '973 _ 15.681.07 15.681.07 

$ 57,179.01 $ 2,308.482.11 $ 2,365.661.12 



SUBTOTAL 
UK 



•"^ '972 I 1 ,350.96 $ 30. 693^46 $ 32.044.42 

^^^'^OJAL $ 1.350.96 $ 30,693.46 $ 32.044.42 
DELTA MOTORS 

II ;S ^ ^30,000.00 $ 430,000.00 

f'Y )965 548.758.00 543 758 00 

'" '966 ^88,157.00 488:f57:00 

SUBTOTAL $ 1.466.915.00 $ 1,466.915.00 
CONSTRUCTION OF FACILITIES (NASA) 

FY i960 (STO) $ 1,200,000.00 $ 1,200 000 00 

FY 1962 1.^3?, 131.43 1.433.131.4^ 

SUBTOTAL $ 2.633.131.43 _______ $ 2.633.131.43 

>VNASA TOTAL $162,592,161.17 $11,691,572.33 $174,283,733.50 



*Does not include subal 1 otinents received nor SRT funds 



30\ 



TABLE LXXI Concluded - SCOUT PROGRAM FY 1973 OBLIGATIONS 

October ] , 1979 

FISCAL YEAR FllNin'; 



AIR FORCE 

*FY i960 
FY 1961 
FY 1962 
FY 1963 
FY 1964 
FY 1965 
FY 1966 
FY 1967 
FY 1968 

FY iq67-8-9-0 (VAFB) 
FY 1969 
FY 1970 
FY 1971 
FY 1972 
FY 1973 

SUBTOTAL 



NAVY 

FY 1 961 
FY 1962 
FY 1965 
FY 1971 

SUBTOTAL 
AEC 

FY 1963 (AL) 
FY 1963 

SUBTOTAL 

REIMBURSABLE TOTALS 

TOTAL 



FY 1972 & PR inp 



$ 5,600.153.78 
1.115,874.28 

10,273,856.95 

6,932,001.20 

963,627.00 

2,742,138.44 

2,025,848.58 

11.591,543.57 

2.883,910.75 

679.281.00 

^84,533.71 
23,716.85 



FY 1973 



TOTAL 



2,908.00 $ 



13,754.00 
3,182.00 



397,334.64 
3,834,269.94 



1 ,020,931.00 

1.988,639.98 

23,5'tl.l7 

^5,962.20 



5,603 

1,115 

10,273 

6.932 

977 

2,745 

2,025 

11,988 

6,718 

679 

m 

1 ,020 

2,012 

23 

45 



,061.78 
,874.28 

.856.95 
,001.20 
.381.00 
.320.44 
,848.58 
,878.21 
,180.69 
281.00 



,533.71 
.931.00 
,356.83 
,541.17 
,962.20 



$ 45,316.486.11 $ 7.330.522.93 $ 52,647-009.04 



$ 1,800,000.00 

7,899,999ol2 

3,348.00 

2.600.00 



0.88 



$ 1,800,000.00 

7,900,000.00 

3,348.00 

2.600.00 



$ 9.705,947.12 $ 



$ 26,563.60 

2.371.000.00 

$ 2.397.56^.60 



0.88 $ 9.705,948.00 



$ 26,563.60 
2.371.000.00 



$ 2.397.563.60 



$ 57,419.996.83 j__^230^j|i^ $ 64.750.520.64 
$220,012,158.00 $ 19,022.096.14 $239,034,254.14 



*609A Program. 



303 



TABLE LXXII - SCOUT PROGRAM FY 1974 OBLIGATIONS 
October 1 , I979 
FISCAL YEAR FUNDS FY 1973 & PRIOR FY 1 97A 

DEVELOPMENT (890) 



FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 



1959 

1959 

i960 

1961 

1962 

1963 

1961 

1962 

1963 



(STG) 



(STO) 
(STO) 
(STO) 



SUBTOTAL 



PRODUCTION (4Qn) 

FY 1961 
FY 1962 
FY 1963 
FY 1964 
FY 1965 
FY 1966 
FY 1967 
FY 1968 
FY 1969 
#FY 1970 
FY 197] 
FY 1972 
FY 1973 
FY 1974 
FY 1965-74 (STO) 

SUBTOTAL 

SEAM (497) 



FY 
FY 
FY 
FY 
FY 
FY 



1964 
1965 
1966 
1967 
1968 
1968 



(STO) 



$ 3,810,488.00 
3,365,593.25 
2,978,043.04 
6,600,000.00 
2,911,217.42 
3,484,149.22 

300,000.00 
1,725,000.00 

402, OOP .nn 

$ 25,576,490.93 



$ 



1,200, 

6,582, 

8.054, 

8,100. 

5,688, 

7,600, 

5.399, 

5,163, 

12,490, 

13,034, 

12,541, 

14,344, 

8.665, 



000.00 

817.92 

000.00 
000.00 

300.00 

000.00 

602.00 

000.00 

988.00 
670.99 

000.00 
000.00 
341.26 



2.553.700.00 



-37.86 
-0.35 

6,794,830.00 

7,317,876.61 

333.000.00 



TOTAL 



$ 3,810,488.00 
3,365,593.25 
2,978,043.04 
6,600,000.00 
2,911,217.42 
3,484,149.22 
300,000.00 
1,725,000.00 
402 .000. on 

$ 25,576,490.93 



$ 1 



,200 

6,582 

8,054 

8,100 

5,688 

7,600 

5,399 

5,163 

12,490 

13.034 

12,540 

14,344 

15,460 

7,317 
2.886 



,000.00 
,817.92 
,000.00 
,000.00 

,300,00 

,000,00 

,602.00 

,000.00 

,988.00 
.633.13 
,999.65 

,000.00 
, 1 7 1 . 26 

,876.61 

.700.00 



$111,417,420.17 $ 14.445,668.40 $125,863,088.57 



$ 3.400,000.00 

7,494,526.42 

3.999,954.00 

3.985,091.00 

4,962,661.35 
^6 nnci nn 



-50.47 



$ 3.400,000.00 
7.494,526.42 

3.999,903.53 
3,985.091.00 

4,962,661.35 
36. 000. 00 



SUBTOTAL 



$ 23,878,232,77 $ 



-50.47 $ 23,878,182,30 



?lncludes San Marco. 



304 
TABLE LXXII Continued - SCOUT PROGRAM FY 1974 OBLIGATIONS. 









October 1 , 1979 








FISCAL YEAR FUNDS 


FY 


1973 & PRIOR 




FY 1974 




TOTAL 


SAN MARCO 
















FY 1963 

FY 1964 

FY 1965 

FY 1966 

FY 1967 

FY 1968 

FY 1964 Trust 

FY 1965 Trust 

FY 1967 Trust 

FY 1969 Trust 

FY 1970 Trust 

FY 1973 Trust 


Fund 
Fund 
Fund 
Fund 
Fund 
Fund 


$ 


1,865,915.72 

337,733.13 

500,000.00 

350,000.00 

100,000.00 

70,000.00 

200,000.00 

478,917.00 

29.672.84 

48,009.06 

243,258.92 

478.695.04 


$ 


1,548.00 

6,741.08 
779.436.52 


$ 


1,865,915.72 
337,733.13 
500,000.00 
350,000.00 
100,000.00 

70,000.00 

200,000.00 

480,465.00 

29,672.84 

48,009.06 

250,000.00 

1,258,131.56 


SUBTOTAL 




$ 


4,702,201.71 


$ 


787,725.60 


$ 


5,489,927.31 


ESRO IB 
















FY 1970 
FY 1971 




$ 
$ 


1,861,635,95 
350.000.00 

2,211,635.95 


$ 


93.17 


$ 
$ 


1,861,729.12 
350.000.00 


SUBTOTAL 


$ 


93.17 


2,211,729.12 


ESRO IV 
















FY 1970 
FY 1971 
FY 1972 
FY 1973 




$ 


49,980.05 

1,500,000.00 

800,000.00 

15.681.07 


$ 


-201.00 
-31.00 

25.190.12 


$ 


49,779.05 

1,499,969.00 

800,000.00 

40 . 87 1 . 1 9 


SUBTOTAL 




$ 


2,365,661.12 


$ 


24,958.12 


$ 


2,390,619.24 


UK 
















FY 1972 
FY 1973 




$ 


32,044.42 


$ 

$ 


-271.38 
1.230.165.31 

1,229,893.93 


$ 
$ 


31,773.04 
1,230,165.31 


SUBTOTAL 


$ 


32,044.42 


1,261,938.35 


DELTA MOTORS 
















FY 1964 
hY 1965 
FY 1966 




$ 
$ 


430,000.00 
548,758.00 
488.157.00 

1,466,915.00 






$ 


430,000.00 
548,758.00 
488.157.00 


SUBTOTAL 


$ 


1,466,915.00 


CONSTRUCTION OF 


FACILITIES 


(NASA) 










FY i960 (STO; 
FY 1962 


) 


$ 


1,200,000.00 
1.433.131.43 






$ 


1,200,000.00 
1,433, 13'. '+3 


SUBTOTAL 




i- 


2,633,131.43 






1^ 


2.633.131.43 


*NASA TOTAL 




$174,283,733.50 


$ 


16,496,288.75 


$190,780,022.25 



305 

TABLE LXXII Concluded - SCOUT PROGRAM FY IS?'* OBLIGATIONS. 
October 1 , 197$ 

FISCAL YEAR FUNDS FY 1973 & PRIOR FY 1974 JOTAL 

REIMBURSABLE - INTERNATIONAL 

AEROS-B (483) 

^^ '97^ $ 808.770.12 $ 808.770. 12 

S^^'TO'"''^'- $ 808,770.12 $ 808,770.12 

UK-5 (483) 

•"^ '97^* $ 51.870.76 $ 51.870.76 



SUBTOTAL 



51.870.76 $ 51.870.76 



REIMBURSABLE - INTERNATIONAL TOTALS $ 860,640.88 $ 860. 640.88 
AIR FORCE 

:ll |960 $ 5,603,061.78 $ 5,603,061.78 

*FY 961 1,115,874.28 1,115.874.28 

FY 962 10,273,856.95 10.273.856.95 

II 963 6,932,001.20 6,932,001.20 

FV oS .V''^^'-?? 977.381.00 

FY 1965 2,745,320.44 2,745,320.44 

FY 1966 2,025,848.58 2.025,848.58 

''Y 1-^67 11,988,878.21 $ -2,666,762.78 9,322,115.43 

FY '968 6,718,180.69 -300,391.20 6,417.789.49 

FY 1967-8-9-0 (VAFB) 679,281.00 679 281 00 

FY 1969 484,533.71 484!533!7i 

FY 1970 1,020.931.00 

FY 1971 2.012,356.83 -400,098.07 1.612,258.76 

FY 1972 23,541.17 448,33^.83 471,876.00 

FY '973 45.962.20 13.095.38 59,057.58 

FY '974 1.700.001.31 1.700.001.31 

SUBTOTAL $52,647,009.04 S -1,205,820.53 $51,441,188.51 
N AVY 

FY 1961 $ 1,800,000.00 $ 1.800.000.00 

FY 1962 7,500,000.00 7,900,000.00 

FY '965 3,348.00 3.348.00 

FY '971 2.600.00 2.600.00 

SUBTOTAL $ 9,705.9^8.00 $ 9,705,948.00 
AEC 

FY 1963 (AL) $ 26,563.60 $ 26,563.60 

FY '963 2.371.000.00 2.371.000.00 

SUBTOTAL $ 2.397.563.60 ^^^^^^^^^^^^^^^^ $ 2.397.563.60 

REIMBURSABLE TOTALS $ 6.4.750.520.64 $ -1.205.820.53 $ 63.544.700.11 

TOTAL $239,034,254.14 $ 16,143,109.10 $255,177,363.24 



306 





TABLE 


LXXI 1 1 - SCOUT PKUliKAM 


t-Y iy/5 UDLI 








Octobe 


r 1. 1979 


FISCAL YEAR 


FUNDS 


D 


' 1974 & PRIOR 


FY 1975 


DEVELOPMENT 


(890) 








FY 1959 (STG) 


$ 


3,8lO,it88.00 




FY 1959 






3,365.593.25 




FY i960 






2, 978, 0^43. 04 




FY 1961 






6,600,000.00 




FY 1962 






2,911,217.42 




FY 1963 






3,484,149.22 




FY 1961 


(STO) 




300,000.00 




FY 1962 


(STO) 




1,725,000.00 




FY 196^ 


(sTO) 




402.000.00 




SUBTOTAL 




$ 


25,576,490.93 




PRODUCTION 


(^90), 








FY I96I 




$ 


1 ,200,000.00 




FY 1962 






6,582,817.92 




FY 1963 






8,054,000.00 




FY 196^ 






8,100.000.00 




FY 1965 






5,688,300.00 




FY 1966 






7,600,000.00 




FY 1967 






5,399.602.00 




FY 1968 






5,163,000.00 




FY 1969 






12,490,988.00 




#FY 1970 






13,034,633.13 $ 


0.87 


FY 1971 






12.540,999.65 


-934.65 


FY 1972 






14.344,000.00 




FY 1973 






15,460,171.26 


110,828.74 


FY 197^ 






7,317,876.61 


-114,212.87 


FY 1965-75 (STO) 




2,886,700.00 


915,000.00 


FY 1975 








7.130.900.12 


SUBTOTAL 


$125,863,088.57 $ 


8,041,582.21 


SEAM (A 97) 










FY 196^4 




$ 


3,400,000,00 




FY 1965 






7,494,526.42 




FY 1966 






3,999,903.53 




FY 1967 






3,985.091.00 




FY 1968 






4,962,661.35 




FY 1968 


(STO) 




36.000.00 




SUBTOTAL 




$ 


23,878,182.30 





TOTAL 



$ 3,810,488.00 
3,365,593.25 
2,978,043.04 
6,600,000.00 
2, 911, .217. 42 
3,484,149.22 
300,000.00 
1 ,725,000.00 
402.000.00 

$ 25.576,490.93 



1,200 

6,582 

8,054 

8,100 

5,688 

7,600 

5,399 

5,163 

12,490 

13,034 

12,540 

14,344 

15,571 

7,203 

3,801 

7,130 



,000.00 

,817.92 

,000.00 
,000.00 

,300.00 

,000.00 
,602.00 
,000.00 

.988.00 
,634.00 
,065.00 

,000.00 
,000.00 
,663.74 
,700.00 
.900.12 



$133,904,670.78 



$ 3,400,000.00 
7,494,526.42 
3,999,903.53 
3,985,091.00 

4,962,661.35 
36.000.00 

$ 23,878,182.30 



^Includes San Marco. 



ORIGINAL PAGE Si' 
OF POOR QUALITY 



307 



TA3LE LXXIll Continued - SCOUT PROGRAM FY 1975 OBLIGATIONS. 

October 1 , I979 
FISCAL YEAR FUNDS FY 1974 & PRIOR FY 1975 



TOTAL 



SAN MARCO 



FY 1963 

FY 1964 

FY 1965 

FY 1966 

FY 1967 

FY 1968 

FY 1964 Trust 

FY 1965 Trust 

FY 1967 Trust 

FY 1969 Trust 

FY 1970 Trust 

FY 1973 Trust 

FY 1975 Trust 


Fund 
Fund 
Fund 
Fund 
Fund 
Fund 
Fund 


$ 


1,865.915.72 

337.733.13 

500.000.00 

350,000.00 

100,000.00 

70,000.00 

200,000.00 

480,465.00 

29,672.84 

48,009.06 

250,000.00 

1,258,131.56 


$ 

$ 


4,498.93 
454,618.10 


SUBTOTAL 


$ 


5,489,927.31 


459,117.03 


ESRO IB 












FY 1970 
FY 1971 
FY 1975 




$ 


1.861,729.12 

350,000.00 


$ 
$ 


5,545.62 
124.451.46 


SUBTOTAL 


$ 


2,211,729.12 


129,997.08 


ESRO IV 












FY 1970 
FY 1971 
FY 1972 
FY 1973 




$ 


49.779.05 

1,499,969.00 

800,000.00 

40.871.19 


$ 


-2,295.99 
-29,981.06 
-11,640.70 
268.908.19 


SUBTOTAL 




$ 


2,390.619.24 


$ 


224,990.44 


UK-XA 












FY 1972 
FY 1973 
FY 1974 
FY 1975 




$ 


31,773.04 
1,230,165.31 


$ 
$ 


-6,429.92 
-606,9(4.9.14 

1,765,583.28 
187.697.86 


SUBTOTAL 


$ 


1,261,938.35 


1,339,902.08 


DELTA MOTORS 












FY 1964 
FY 1965 
FY 1966 




$ 


430,000.00 
548,758.00 
488,157.00 






SUBTOTAL 




$ 


1 ,466,915.00 






CONSTRUCTION OF 


FACILITIES 


(NASA) 






FY 1 qAd ( <;-ri^' 




c 


( 9An CiCiCi r\r\ 




FY 1362 






1,433, 131. '*3 






SUBTOTAL 




$ 2, 633, 131. '*3 
$190,780,022.25 












*NASA TOTAL 


$ 


10,170,588,84 



$ 1,865,915.72 
337,733.13 

500,000.00 
350,000.00 

100,000.00 

70,000.00 

200,000.00 

480,465.00 

29,672.84 

48,009.06 

250,000.00 

1,262,630.49 

454.618.10 

$ 5,949,044.34 



$ 1,867.274.74 
350,000.00 
124.451.46 

$ 2,341,726.20 



$ 47,483.06 

1,469,987.94 

788,359.30 

30 9,779.38 

$ 2,615,609.68 



$ 25,343.12 

623,216.17 

1,765,583.28 

187,697.86 

$ 2,601,840.43 



5 430,000.00 
548,758.00 
488.157.00 

$ 1 ,466,915,.0O 



3 I , iUU, uliu. uu 

1.433.131.43 
$ 2.633.131.43 
$200,950,611.09 



"'Does not include suba I lotmen ts rece ved nor SRT funds. 



. ^ ■".;-" f 51 



308 



OF POOR QUALITY 



TABLE LXXIll Concluded - SCOUT PROGRAM FY 1975 OBLIGATIONS. 
October 1 , 1979 
FY 197? 



FISCAL YEAR FUNDS FY 1974 S- PRIOR 

REIMBURSABLE - INTERNATIONAL 
AEROS-B (483) 



FY 1974 
FY 1975 

SUBTOTAL 

UK-5 (483) 

FY 1974 
FY 1975 

SUBTOTAL 



$ 808,770.12 $ 



1.675,872.81 
964.631.79 



$ 808,770.12 $ 2,640,504.60 



51,870.76 $ 



68.01 
18.636.02 



$ 51.870.76 i. 



18.704.03 



REIMB-INTERNAT'L 


TOTALS 


$ 


860,640.88 


$ 


2,659,208.63 


AIR FORCE 












*FY i960 
*FY 1961 

FY 1962 

FY 1963 

FY 1964 

FY 1965 

FY 1966 

FY 1967 

FY 1968 

FY 1967-8-9-0 

FY 1969 


(VAFB) 


$ 


5,603,061.78 
1,115,874.28 

10,273,856,95 

6,932,001.20 

977,381.00 

2,745,320.44 

2,025,848.58 

9,322,115.43 

6,417,789.49 

679,281.00 

484,533.71 


$ 


-112.42 

2,025,087.99 

349.19't.'t5 

-210,350.53 


FY 1970 
FY 1971 
FY 1972 
FY 1973 
FY 1974 
FY 1975 






1,020,931.00 

1,612,258.76 

471 ,376.00 

59,057.58 

1 ,700,001 .31 




-1 ,420,279.02 

-326,229.72 

-32,638.14 

1 ,676,178.40 

741,579.96 


SUBTOTAL 


$ 


51 ,441 ,188.51 


$ 


2,802,430.97 


NAVY 












FY 1961 
FY 1962 
FY 1965 
FY 1971 
FY 1975 




$ 


1,800,000.00 

7,900,000.00 

3,348.00 

2,600.00 


1. 
$ 


65.000.00 


SUBTOTAL 


$ 


9,705,948.00 


65,000.00 


AEC 












FY 1963 (AL) 
FY 1963 
FY 1974 




$ 


26,563.60 
2,371,000.00 




220.000.00 


SUBTOTAL 


L 


2.397.563.60 


220.000.00 


REIMBURSABLE TOT 


ALS 


$ 63. 5')'*. 700. 11 


? 


3.087.430.97 


TOTAL 


$255,177,363.24 


$ 


15,942,228.44 



TOTAL 



$ 2,484,642.93 
q64.631.79 

$ 3.449,274.72 



$ 51,938.77 
18^636.02 

$ 70.574JJ 

$ 3.519.849.51 



$ 5.603,061.78 

1,115,874.28 

10,273,856.95 

6,932,001.20 

977,381.00 

2,745,320.44 

2,025,736.16 

11,347,203.42 

6,766,983.9^+ 

679,281.00 

274,183.18 

1 ,020,931.00 

191.979.7't 

145,646.28 

26,4l9.4'i 

3,376,179.71 
741 ,579.96 

$ 54,243,619.48 



$ 1,800,000.00 

7,900,000.00 

3,348,00 

2,600.00 

65.000.00 

$ 9,770,948.00 



$ 26,563.60 

2,371,000.00 

220.000.00 

1 2.617.563.60 

$ 66.6j2..131.08 

$271,119,591.68 



*609A Program. 



309 





TABLE 


LXXIV - SCOUT PRO! 
October 1 , 


SRAM FY 1 
1979 


976 OBLi 


CATIONS. 


FISCAL YEAR FUNDS 


FY 1975 & PRIOR 


FY 


1976 


TOTAL 


DEVELOPMENT (890) 










FY 1959 


(STG) 


$ 3,810,488.00 






$ 3.810,488.00 


FY 1959 




3.365,593.25 






3,365,593.25 


FY I960 




2,978,043.04 






2,978,043.04 


FY 1961 




6,600,000.00 






6,600,000.00 


FY 1962 




2,911,217.42 






2,911,217.42 


FY 1963 




3,484,149.22 






3,484,149.22 


FY 1961 


(STO) 


300,000.00 






300,000.00 


FY 1962 


(STO) 


1,725,000.00 






1,725,000.00 


FY 1963 


(STO) 


402,000.00 






402.000.00 


SUBTOTAL 




$25,576,490.93 






$ 25,576,490.93 


PRODUCTION 


(490) 










FY 1961 




$ 1,200,000.00 






$ 1,200,000.00 


FY 1962 




6,582,817.92 






6,582,817.92 


FY 1963 




8,054,000.00 






8,054,000.00 


FY 1964 




8,100,000.00 






8,100,000.00 


FY 1965 




5,688,300.00 






5,688,300.00 


FY 1966 




7,600,000.00 






7,600,000.00 


FY 1967 




5,399.602.00 






5,399,602.00 


FY 1968 




5,163,000.00 






5,163,000.00 


FY 1969 




12,490,988.00 






12,490,988.00 


#FY 1970 




13,034,634.00 






13,034,634.00 


FY 1971 




12,540,065.00 






12,540,065.00 


FY 1972 




14,344,000.00 






14,344,000.00 


FY 1973 




15,571,000.00 






15.571.000.00 


FY 1974 




7,203,663.74 


$ 254,975.79 


7,458,639.53 


FY 1965- 


76 (STO) 


3,801,700.00 


119 


,000.00 


3,920,700.00 


FY 1975 




7,130,900.12 


4,238,879.88 


11,369,780.00 


FY 1976 






7.007.680.97 
$11,620,536.64 


7.007.680.97 


SUBTOTAL 


$133,904,670.78 


$145,525,207.42 


SEAM (if97) 












FY 1964 




$ 3,400,000.00 






$ 3,400,000.00 


FY 1965 




7,494,526.42 






7,494,526.42 


FY 1966 




3,999,903.53 






3.999.903.53 


FY 1967 




3,985,091.00 






3.985.091.00 


FY 1968 




4,962,661.35 




$0.65 


4,962,662.00 


FY 1968 


(STf^ 


36,000.00 
$23,878,182.30 






36,000.00 


SUBTOTAL 


$0.65 


$23,878,182.95 



#includes San Marco. 



310 



TABLE LXXIV Continued - SCOUT PROGRAM FY 1976 OBLIGATIONS. 
October ], 1979 



FISCAL YEAR FUNDS 



FY 1975 & PRIOR 



FY 1976 



TOTAL 



SAN MARCO 










FY 1963 




$1,865,915.72 




$1,865,915.72 


FY 196'^ 




337,733.13 




337,733.13 


FY 1965 




500,000.00 




500,000.00 


FY 1966 




350,000.00 




350,000.00 


FY 1967 




100,000.00 




100,000.00 


FY 1968 




70,000.00 




70,000.00 


FY 1964 Trust 


Fund 


200,000.00 




200,000.00 


FY 1965 Trust 


Fund 


480, 465. 00 




480,465.00 


FY 1967 Trust 


Fund 


29.672.84 




29,672.84 


FY 1969 Trust 


Fund 


48,009.06 




48,009.06 


FY 1970 Trust 


Fund 


250,000.00 




250,000.00 


FY 1973 Trust 


Fund 


1,262,630.49 


$ 13.95 


1 ,262.644.44 


FY 1975 Trust 


Fund 


454,618.10 


198,981.90 


653,600.00 


SUBTOTAL 




$5,949,044.34 


$198,995.85 


$6,148,040.19 


ESRO IB 










FY 1970 




$1,867,274.74 


$ 5,505.20 


$1,872,779.94 


FY 1971 




350.000.00 




350,000.00 


FY 1975 




124,451.46 


76.702.47 


201,153.93 


SUBTOTAL 




$2,341,726.20 


$ 82,207.67 


$2,423,933.87 


ESRO IV 










FY 1970 




$ 47.483.06 


$ 32,508.00 


$ 79,991.06 


FY 1971 




1,469,987.94 


21.00 


1,470,008.94 


FY 1972 




788,359.30 




788,359.30 


FY 1973 




309,779.38 


25,916.29 


335,695.67 


FY 1976 






781,116.47 
$839,561.76 


781.116.47 


SUBTOTAL 


$2,615,609.68 


$3,455,171.44 


UK-X4 










FY 1972 




$ 25.343.12 


$ 20,739.52 


$ 46,082.64 


FY 1973 




623,216.17 


667,168.19 


1,290.384.36 


FY 197^* 




1,765,583.28 


-105,816.76 


1.659,766.52 


FY 1975 




187,697.86 


342,943.32 


530,641.18 


FY 1976 






9,347.21 
$934,381.48 


9,347.21 


SUBTOTAL 


$2,601,840.43 


$3,536,221.91 


DELTA MOTORS 










FY 196'+ 




$ 430,000.00 




$ 430,000.00 


FY 1965 




548,758.00 




548,758.00 


FY 1966 




488.157.00 




488,157.00 


SUBTOTAL 




$1,466,915.00 




$1,466,915.00 


CONSTRUCTION OF 


FACILITIES 






FY i960 (STO) 




$1,200,000.00 




$1,200,000.00 


FY 1962 




1,433,131.43 




1.433.131.43 


SUBTOTAL 




$2,633,131.43 




$2,633,131.43 


-•--NASA TOTAL 


$200,950,611.09 


$13,666,684.05 


$214,617,295.14 



-"Does not include subaltotments received nor SRT funds. 



ORIGINAL PAGE 13 
OF POOR QUALITY 



311 



TABLE LXXIV 


Concluded - SCOUT 


PROGRAM FY 1976 


OBLIGATIONS. 




October 1 , 


1979 




FISCAL YEAR FUNDS 


FY 1975 & PRIOR 


FY 1_926 


TOTAL 


REIMBURSABLE - INTERNATIONAL 






AEROS-B C+SB) 








FY 197't 


$2,484,642.93 


$ 19,639.85 


$2,504,282.78 


FY 1975 


964,631.79 


-3,584.16 


961,047.63 


FY 1976 




22,948.02 
$ 39,003.71 


22,948.02 


SUBTOTAL 


$3,449,274.72 


$3,488,278.43 


UK-5 (hB3) 








FY 197't 


$ 51,938.77 


$ 6, 416.23 


$ 58,355.00 


FY 1975 


18,636.02 


46,363.98 


65,000.00 


FY 1974 (STO) 




73 7,956.00 
$790,736.21 


737,956.00 


SUBTOTAL 


$ 70,574.79 


$ 861,311.00 


UK-6 (483) 








FY 1975 




$ 19.55 


$ 19.55 


FY 1976 




1,266.53 


1,266.53 


SUBTOTAL 




$ 1,286.08 
$831,026.00 


$ 1,286.08 


REIMB-INTERNAT'L TOTALS 


$3,519,849.51 


$4,350,875.51 


AIR FORCE 








■•FY I960 


$ 5,603,061.78 




$ 5.603.061.78 


■■-FY 1961 


1,115,874.28 




1.115,874.28 


FY 1962 


10,273,856.95 




10,273,856.95 


FY 1963 


6,932,001.20 




6,932.001.20 


FY 1964 


977,381.00 




977,381.00 


FY 1965 


2,745.320.44 




2.745.320.44 


FY 1966 


2,025,736.16 


$ 111.42 


2.025.847.58 


FY 1967 


11,347,203.42 


-2,511,946.99 


8,835.256.43 


FY 1968 


6,766,983.94 


696,092.06 


7,463,076.00 


FY 1967-8-9-0(VAFB) 


679,281.00 




679,281.00 


FY 1969 


274,123.18 


210,350.53 


484,533.71 


FY 1970 


1,020,931.00 




1.020,931.00 


FY 1971 


191,979.74 


84,970.00 


276,949.74 


FY 1972 


145,646.28 


66,316.35 


211,962.63 


FY 1973 


26,419.44 


-442.48 


25,976.96 


FY iy74 


3,376,179.71 


242,768.75 


3,618,948.46 


FY 1975 


741,579.96 




741,579.96 


FY 1976 




40,746.94 
$-1,171,033.42 


40,746.94 


SUBTOTAL 


$54,243,619.48 


$53,072,586.05 


NAVV 








FY 1961 


$1,800,000.00 




$1,800,000.00 


FY 1962 


7,900,000.00 




7,900,000.00 


FY 1965 


3,348.00 




3,348.00 


FY 1971 


2,600.00 




2,600.00 


FY 1975 


65,000.00 




65,000.00 


SUBTOTAL 


$9,770,948.00 




$9,770,948.00 


AEC 








FY 1963 (AL) 


S 26,563.60 




$ 26,563.60 


FY 1963 


2,371 ,000.00 




2,371,000.00 


FY 1974 


220,000.00 




220,000.00 


SUBTOTAL 


$2,617,563.60 
$66,632,131.08 




$2,617,563.60 


REIMBURSABLE TOTALS 


$-!,!71,033.42 


$65,461,097.66 



TOTAL 



$271,119,591.68 $13,335,676.63 $284,455,268.31 



■.■■•609A Program. 



312 



TABLE LXXV - SCOUT PROGRAM FY 197T OBLIGATIONS, 
October 1 , 1979 



FISCAL YEAR FUNDS 



FY 1976 & PRIOR 



FY 197T 



DEVELOPMENT (890) 






FY 1959 (STG) 


$ 3,8l0,'t88.00 




FY 1959 


3,365,593.25 




FY I960 


2,978,0^3.0i» 




FY 1961 


6,600,000.00 




FY 1962 


2,911 ,217-''»2 




FY 1963 


3,'»84,U9.22 




FY 1961 (STO) 


300,000.00 




FY 1962 (STo) 


1 ,725,000.00 




FY 1963 (STo) 


^02,000.00 




SUBTOTAL 


$25,576,490.93 




PRODUCTION (i»90) 






FY 1961 


$ 1,200,000.00 




FY 1962 


6,582,817.92 




FY 1963 


8, OS**, 000. 00 




FY 196*4 


8,100,000.00 




FY 1965 


5,688,300.00 




FY 1966 


7,600,000.00 




FY 1967 


5,399.602.00 




FY 1968 


5,163,000.00 




FY 1969 


12,'»90,988.00 




#FY 1970 


13,03't,63'».00 




FY 1971 


12,5'»0,065.00 




FY 1972 


14, 34'*, 000. 00 




FY 1973 


15,571,000.00 




FY 197^ 


7,458,639.53 




FY 1965-7T (STO) 


3,920,700.00 


$ 3,000.00 


FY 1975 


11,369,780.00 


14,770.00 


FY 1976 


7,007,680.97 


1 ,629,241.06 


FY 197T 




431 ,726.62 


SUBTOTAL 


$145,525,207.42 


$ 2,078,737.68 


SEAM('»97) 






FY 196'* 


$ 3,400,000.00 




FY 1965 


7,494,526.42 




FY 1966 


3,999,903.53 




FY 1967 


3,985,091-00 




FY 1968 


4,962,662.00 




FY 1968 (STO) 


36,000.00 




SUBTOTAL 


$23,878,182.95 





TOTAL 



3,810 
3,365 
2,978 
6,600 
2,911 
3,484 

300 
1,725 

402 



,488.00 
.593.25 
,043.04 
,000.00 
,217.42 
,149.22 
,000.00 
,000.00 
,000.00 



$25,576,490.93 



; 1,200 
6,582 

8,054 

8,100 

5,688 

7,600 

5,399 

5,163 

12,490 

13,034 

12,540 

14,344 

15,571 

7.458 

3,923 

11,384 

8,636 

431 



,000.00 

,817.92 

,000.00 
,000.00 

,300.00 

,000.00 
,602.00 
,000.00 

,988.00 
,634.00 
,065.00 

,000.00 
,000.00 

,639.53 
,700.00 

,550.00 

,922.03 

,726.62 



$147,603.9^5.10 



$ 3,400,000.00 
7,494,526.42 
3.999.903.53 
3,985,091.00 
4.962,662.00 
36,000.00 

$23,878,182.95 



^Includes San Marco. 



313 

TABLE LXXV Continued - SCOUT PROGRAM FY 197T OBLIGATIONS, 
October 1, )979 

FISCAL YEAR FUNDS FY I976 & PRIOR FY 197T 



SAN MARCO 










FY 1963 




$ 1,865,915.72 






FY 1964 




337,733.13 






FY 1965 




500,000.00 






FY 1966 




350,000.00 






FY 1967 




100,000.00 






FY 1968 




70,000.00 






FY 196') Trust 


Fund 


200,000.00 






FY 1965 Trust 


Fund 


't80,'*65.00 






FY 1967 Trust 


Fund 


29, 672. Sit 






FY 1969 Trust 


Fund 


48,009.06 






FY 1970 Trust 


Fund 


250,000.00 






FY 1973 Trust 


Fund 


1 ,262, 644. 44 






FY 1975 Trust 


Fund 


653,600.00 






SUBTOTAL 




$ 6,148.040.19 






ESRO IB 










FY 1970 




$ 1,872,779.94 


$ 


12,310.10 


FY 1971 




350,000.00 






FY 1975 




201,153.93 





29,991.06 


SUBTOTAL 




$ 2,423,933.87 


$ 


42,301.16 


ESRO IV 










FY 1970 




$ 79,991.06 


$ 


-26,129.39 


FY 1971 




1 ,470,008.94 




29,991.06 


FY 1972 




788,359.30 






FY 1973 




335,695.67 




-3,946.21 


FY 1976 




781,116.47 





44,535.00 


SUBTOTAL 




$ 3, 455, 171. H 


$ 


44,450.46 


UK-X^t 










FY 1972 




$ 46,082.64 


$ 


-235.20 


FY 1973 




1,290,384.36 




50,125.44 


FY I97A 




1,659,766.52 






FY 1975 




530,641.18 






FY 1976 




9,3't7.21 





-8,738.26 


SUBTOTAL 




$ 3,536,221.91 


$ 


41 ,151.98 


DELTA MOTORS 










FY 196'( 




$ 430,000.00 






FY 1965 




548,758.00 






FY 1966 




488,157.00 






SUBTOTAL 




$ 1 ,466,915.00 






CONSTRUCTION OF 


FACILITIES 






FY I960 (STO) 




$ 1 ,200,000.00 




FY 1962 




1,'*33,131.43 






SUBTOTAL 




$ 2.633,131.43 
$214,617,295.14 






NASA TOTAL 


$2 


206,641.28 



TOTAL 



$ 1,865,915.72 

337,733.13 

500,000.00 

350,000.00 

100,000.00 

70,000.00 

200,000.00 

480,465.00 

29,672.84 

48,009.06 

250.000.00 

1.262.644.44 

653,600.00 

$ 6.148.040.19 



$ 1 .885,090.04 
350,000.00 
231 ,144.99 

$ 2,466,235.03 



$ 53,861.67 

1 ,500,000.00 

788,359.30 

331 ,749.46 

825,651.47 

$ 3,499,621.90 



$ 45,847.44 

l,3'tO,509.80 

1,659,766.52 

530,641.18 

608.95 

$ 3,577,373.89 



$ 430.000.00 
548,758.00 
488,157-00 

$ 1,466.915.00 



$ 1 ,200.000.00 
1,433,131.43 

$ 2.633,131-43 
$216,823,936.42 



Jc^^s not include suba 1 loLnien ts received nor SRT funds. 



31it 

TABLE LXXV Continued - SCOUT PROGRAM FY 197T OBLIGATIONS. 
October 1 , 1979 

FISCAL YEAR FUNDS FY 1976 S PRIOR FY 197T TOTAL 



REIMBURSABLE - INTERNATIONAL 






AEROS-B (483) 










FY 1974 


$ 


2.504,282.78 


$ 


-73.952.65 


FY 1975 




961,047.63 




24.721.57 


FY 1976 




22,948.02 




1.831.15 


SUBTOTAL 


$ 


3.488,278.43 


$ 


-47.409.93 


UK-5 (483) 










FY 1974 


$ 


58.355.00 






FY 1975 




65,000.00 






FY 1976 






$ 


11.307.15 


FY 1974 (STO) 


$ 


737.956.00 
861.311.00 






SUBTOTAL 


$ 


11.307.15 


UK-6 (483) 










FY 1975 


$ 


19.55 


$ 




FY 1976 




1 ,266.53 




16.54 


FY 197T 






$_ 


1,305.00 


SUBTOTAL 


$_ 


1 ,286.08 


1.321.54 


REIMB-INTERNAT'L TOTAL 


$ 


4,350,875.51 


$ 


-34.781.24 


AIR FORCE 










^VFY I960 


$ 


5,603,061.78 


$ 




=--FY 1961 




1,115.874.28 






FY 1962 




10,273,856.95 






FY 1963 




6,932,001.20 






FY 1964 




977.381.00 






FY 1965 




2,745.320.44 






FY 1966 




2.025,847.58 






FY 1967 




8,835.256.43 




426.594.91 


FY 1968 




7,463.076.00 




-10.697.75 


FY 1967-8-9-0 (VAFB) 




679,281.00 






FY 1969 




484,533.71 






FY 1970 




1 ,020,931.00 






FY 1971 




276,949.74 




31.451.00 


FY 1972 




211 ,962.63 






FY 1973 




25.976.96 




-8,354.98 


FY 1974 




3,618,948.46 




-717.620.79 


FY 1975 




741.579-96 




494,387.33 


FY 1976 




40,746.94 




386,765.12 


FY 197T 






$ 


12,003.52 


SUBTOTAL 


$ 


53.072.586.06 


614,528.36 


NAVY 










FY 1961 


$ 


1 ,800,000.00 


S 




FY 1962 




7.900.000.00 






FY 1965 




3,348.00 






FY 1971 




2,600.00 






FY 1975 




65,000.00 






SUBTOTAL 


$ 


9,770,948.00 






■-'•6O9A Program. 





$ 2,430,320.13 
985.769.20 

24,779-17 
$ 3.440,868.50 



$ 58,355.00 

65,000.00 

11,307.15 

737.956.00 

$ 872.618.15 



$ 19.55 

1.283.07 

1 .305.00 

$ 2.607.62 

$ 4,316,094.27 



$ 5,603.061.78 

1 .115,874.28 

10.273.856.95 

6,932,001.20 

977,381.00 

2.745,320.44 

2.025,847-58 

9.261,851.34 

7.452.378.25 

679,281.00 

484.533.71 

1.020.931.00 

308.400.74 

211.962.63 

17,621.98 

2,901.327.67 

1.235,967.29 

427,512.06 

12.003.52 

$53,687,114.42 



$ 1 ,800,000.00 

7,900,000.00 

3.348.00 

2.600.00 

65,000.00 

$ 9,770,948.00 



315 



TABLE LXXV Concluded - SCOUT PROGRAM FY 197T OBLIGATIONS. 
October 1 , 1979 



FISCAL YEAR FUNDS 

REIMBURSABLE - POD 

AEC 

FY 1963 (AL) 
FY 1963 

FY ig?** 

SUBTOTAL 

REIMBURSABLE TOTALS 
TOTAL 



FY 1976 S Prior 



$ 26,563.60 

2,371,000.00 

220,000.00 

$ 2,617,563.60 



FY 197T 



$ 65,461,097.66 $ 614,528-36 
$284,it55,268.31 $2,786,388.40 



TOTAL 



$ 26,563.60 

2,371,000.00 

200,000.00 

$ 2,617,563.60 

$ 66,075,626.02 
$287,241,656.71 



316 



TABLE LXXVI - SCOUT PROGRAM FY 1977 OBLIGATIONS. 
October 1 , 1979 



FISCAL YEAR FUNDS 



DEVELOPMENT (89O) 



FY 197T & PRIOR 



FY 1977 



TOTAL 



FY 


1959 


(STG) 


FY 


1959 




FY 


i960 




FY 


1961 




FY 


1962 




FY 


1963 




FY 


1961 


(STO) 


FY 


1962 


(STO) 


FY 


1963 


(STO) 


SUBTOTAL 




PRODUCTION 


(490) 


FY 


1961 




FY 


1962 




FY 


1963 




FY 


1964 




FY 


1965 




FY 


1966 




FY 


1967 




FY 


1968 




FY 


1969 




#FY 


1970 




FY 


1971 




FY 


1972 




FY 


1973 




FY 


197't 




FY 


1965- 


77 (STO) 


FY 


1975 




FY 


1976 




FY 


197T 




FY 


1977 




SUBTOTAL 




SEAM 


(^♦97) 




FY 


196'+ 




FY 


1965 




FY 


1966 




FY 


1967 




FY 


1968 




FY 


1968 


(STO) 


SUBTOTAL 





3,810 
3,365 
2,978 
6,600 
2,911 
3,484 

300 
1,725 

402 



,488.00 
,593.25 
,043.04 
,000.00 
,217.42 
,149.22 
,000.00 
,000.00 
.000.00 



$25,576,490.93 



$ 1,200,000.00 




6,582,817.92 




8,054,000.00 




8,100,000.00 




5,688,300.00 




7,600,000.00 




5.399,602.00 




5,163,000.00 




12,490,988.00 




13,034,634.00 




12,540.065.00 




14,344,000.00 




15,571 ,000.00 




7.458,639.53 


$ -15,006.30 


3,923.700.00 


359,000.00 


11,384,550.00 





8.636,922.03 


1,819,077.97 


431,726.62 


2,965,273.38 





6,911 .182.38 


$147,603,945.10 


$12,039,527.85 


$ 3.400,000,00 




7,494,526.42 




3,999.903.53 




3,985,091.00 




4,962,662.00 


$ -130.80 


36,000.00 





$23,878,182.95 


$ -130.80 



3.810 
3,365 
2,978 
6,600 
2.911 
3.484 

300 
1.725 

402 



.488.00 
.593.25 
.043.04 
,000.00 
,217.42 
,149.22 
.000.00 
,000.00 
.000.00 



$25,576,490.93 



1,200 

6.582 

8,054 

8,100 

5.688 

7,600 

5,399 

5,163 

12.490 

13,034 

12,540 

14,344 

15,571 

7,443 

4,282 

11,384 

10,456 

3,397 

6.911 



.000.00 

,817.92 

,000.00 
,000.00 

,300.00 

,000.00 

,602.00 

.000.00 

,988.00 

,634.00 

,065.00 

,000.00 
,000.00 

,633.23 
,700.00 
,550.00 

,000.00 
,000.00 
,182.80 



$159,643,472.95 



$ 3,400,000.00 
7.494,526.42 
3,999,903.53 
3.985,091.00 
4.962,531.20 
36,000.00 

$23,878,052.15 



#lncludes San Marco. 



317 



TABLE LXXVI Continued - SCOUT PROGRAM FY 1977 OBLIGATIONS. 
October 1 , 1979 



FISCAL YEAR FUNDS 


FY 197T & PRIOR 




FY 1977 


SAN MARCO 










FY 1963 




$1,865,915.72 






FY 1964 




337,733.13 






FY 1965 




500,000.00 






FY 1966 




350,000.00 






FY 1967 




100,000.00 






FY 1968 




70,000.00 






FY 1964 Trust 


Fund 


200,000.00 






FY 1965 Trust 


Fund 


480,465.00 






FY 1967 Trust 


Fund 


29,672.84 






FY 1969 Trust 


Fund 


48,009.06 






FY 1970 Trust 


Fund 


250,000.00 






FY 1973 Trust 


Fund 


1,262,644.44 


$ 


2.80 


FY 1975 Trust 


Fund 


653.600.00 







SUBTOTAL 




$6,148,040.19 


$ 


2.80 


ESRO IB 










FY 1970 




$1,885,090.04 


$ 


17,680.96 


FY 1971 




350,000.00 







FY 1975 




231.144.99 




-20,488.99 


SUBTOTAL 




$2,466,235.03 


$ 


-2,808.03 


ESRO IV 










FY 1970 




$ 53,861.67 


$ 


-3,861.67 


FY 1971 




1,500,000.00 







FY 1972 




788,359.30 




11,640.70 


FY 1973 




331,749.46 




84.54 


FY 1976 




825,651.47 




85,515.53 


SUBTOTAL 




$3,499,621.90 


$ 


93,379.10 


UK-X4 










FY 1972 




$ 45,847.44 


$ 


4,152.56 


FY 1973 




1,340,509.80 




4.863.20 


FY 1974 




1,659,766.52 




36,019.27 


FY 1975 




530,641.18 




148,977.48 


FY 1975 DIRECT 








76,988.00 


FY 1976 




608.95 




-637.78 


SUBTOTAL 




$3,577,373.89 


$ 


270,362.73 


DELTA MOTORS 










FY 1964 




$ 430,000.00 






FY 1965 




548,758.00 






FY 1966 




488.157.00 






SUBTOTAL 




$1,466,915.00 






CONSTRUCTION OF 


FACILITIES 






FY i960 (STO) 




$ 1,200,000,00 






FY 1962 




1.433.131.43 






SUBTOTAL 




$ 2.633.131.43 
$216,823,936.42 






--NASA TOTAL 


$12 


,073,345.65 



TOTAL 



$1,865,915.72 

337,733.13 

500,000.00 

350,000.00 

100,000.00 

70,000.00 

200,000.00 

480,465.00 

29,672.84 

48,009.06 

250,000.00 

1,262,647.24 

653.600.00 

$6,148,042.99 



$1,902,771.00 
350,000.00 
210.656.00 

$2,463,427.00 



$ 50,000.00 

1 ,500,000.00 

800,000.00 

331,834.00 

911.167.00 

$3,593,001.00 



$ 50,000.00 

1,345,373.00 

1.695,785.79 

679,618.66 

76,988.00 

-28.83 

$3,847,736.62 



$ 430,000.00 
548,758.00 
488,157.00 

$1,466,915.00 



$ 1,200,000.00 
1.433.131.43 

$ 2.633.131.43 

$228,897,282.07 



"Does not include subal lotments received nor SRT funds. 



318 



TABLE LXXVI Continued - SCOUT PROGRAM FY 1977 OBLIGATIONS. 
October 1 , 1979 



FISCAL YEAR FUNDS 



FY 197T £■ PRIOR 



REIMBURSABLE - INTERNATIONAL 


AEROS-B (483) 




FY 1974 


$2,430,320.13 


FY 1975 


985,769.20 


FY 1976 


24,779.17 


FY 1977 





SUBTOTAL 


$3,440,868.50 


UK-5 (483) 




FY 1974 


$ 58,355.00 


FY 1975 


65,000.00 


FY 1976 


11.307.15 


FY 1974 (STO) 


737.956.00 


SUBTOTAL 


$ 872.618.15 


UK-6 (483) 




FY 1975 


$ 19.55 


FY 1976 


1,283.07 


FY 197T 


1,305.00 


FY 1977 





SUBTOTAL 


$ 2,607.62 


REIMB-INTERNAT'L TOTAL 


$4,316,094.27 


AIR FORCE 




-VFY I960 


$ 5.603,061.78 


-VFY 1961 


1,115,874.28 


FY 1962 


10,273,856.95 


FY 1963 


6,932,001.20 


FY 1954 


977,381.00 


FY 1965 


2,745,320.44 


FY 1966 


2.025.847.58 


FY 1967 


9,261,851.34 


FY 1968 


7,452,378.25 


FY 1967-8-9-0 (VAFB) 


679.281 .00 


FY 1969 


484.533.71 


FY 1970 


1.020,931.00 


FY 1971 


308,400.74 


FY 1972 


211,962.63 


FY 1973 


17.621.98 


FY 1974 


2,901.327.67 


FY 1975 


1.235,967.29 


FY 1976 


427,512.06 


FY 197T 


12,003.52 


FY 1977 





SUBTOTAL 


$53,687,114.42 


NAVY 




FY 1961 


$1 ,800,000.00 


FY 1962 


7,900,000.00 


R 1965 


3,348.00 


FY 1971 


2,600.00 


FY 1975 


65.000.00 


SUBTOTAL 


$9,770,948.00 



FY 1977 



TOTAL 



$ 209,679.87 

113,010.09 

-162.00 

20,500.29 

$ 343,028.25 



-30,00 






-30.00 



$ 30,610.84 

4.98 

-6.43 

3.875.60 

$ 34.484.99 
$ 377.483.24 



$2,729,148.66 

10.697.75 









390.545.37 

46,529.02 

-244,026.15 

54,032.71 

1,227,981.43 

-468.91 

3.747.17 

$4,218,187.05 



$2,640,000.00 

1.098,779.29 

24,617.17 

20.500.29 

$3,783,896.75 



$ 58,325.00 

65,000.00 

11.307.15 

737.956.00 

$ 872,588.15 



$ 30,630.39 
1,288.05 
1,298.57 
3.875.60 

$ 37.092.61 

$4,693,577.51 



$ 5,603 

1.115 

10,273 

6,932 

977 

2,745 

2,025 

11,991 

7,463 

679 

484 

1,020 

308 

602 

64 

2,657 

1,290 

1,655 

11 

3 



,061 .78 
,874.28 
.856.95 
,001,20 
,381.00 
.320.44 
.847.58 
,000.00 
,076,00 
,281 ,00 
,533.71 
,931.00 
,400.74 

.508,00 
,151.00 
,301.52 

,000,00 

.493.49 
.534.61 
.747.17 



$57,905,301.47 



$1,800,000.00 

7,900,000.00 

3,348.00 

2,600,00 

65.000,00 

$9,770,948,00 



319 

TABLE LXXVI Concluded - SCOUT PROGRAM FY 1977 OBLIGATIONS. 
October 1, 1979 



FISCAL YEAR FUNDS 


FY 197T S Prior 


FY 1977 




TOTAL 


REIMBURSABLE - DOO 










AEC 










FY 1963 (AL) 


$ 26,563.60 






$ 26,563.60 


FY 1963 


2,371,000.00 






2,371,000.00 


FY 197^* 


220,000.00 






200,000.00 


SUBTOTAL 


$ 2,617,563.60 
$ 66,075,626.02 




1 


$ 2.617.563.60 


REIMBURSABLE TOTALS 


$ 4,218,187.05 


$ 67.293,813.07 


TOTAL 


$287,241,656.71 


$16,996,003.9^ 


^ 


$304,237,660.65 


TABLE LXXVII - SCOUT 


PROGRAM FY 1978 


OBLIGATIONS. 


DEVELOPMENT (890) 


FY 1977 e PRIOR 
$ 3,810,488.00 


FY 1978 


- 


TOTAL 


FY 1959 (STG) 




$ 3.810.488.00 


FY 1959 


3,365,593.25 






3.365.593.25 


FY I960 


2,978,043.04 






2.978,043.04 


FY 1961 


6,600,000.00 






6,600,000.00 


FY 1962 


2,911,217.42 






2,911.217.42 


FY 1963 


3,484,149.22 






3,484,149.22 


FY 1961 (STO) 


300,000.00 






300,000.00 


FY 1962 (STO) 


1,725,000.00 






1 ,725,000.00 


FY 1963 (STO) 


402,000.00 






402,000.00 


SUBTOTAL 


$25,576,490.93 






$25,576,490.93 


PRODUCTION (490) 










FY 1961 


$ 1,200,000.00 






$ 1,200,000.00 


FY 1962 


6. 582. 817.92 






6,582,817.92 


FY 1963 


8,054,000.00 






8,054,000.00 


FY 196^+ 


8,100,000.00 






8,100,000.00 


FY 1965 


5,688,300.00 






5,688,300.00 


FY 1966 


7,600.000.00 






7,600,000.00 


FY 1967 


5,399,602.00 






5^,399,602.00 


FY 1968 


5,163,000.00 






5,163,000.00 


FY 1969 


12,490,988.00 






12,490,988.00 


#FY 1970 


13.034.634.00 






13,034,634.00 


#FY 1971 


12,540,065,00 






12,540,065.00 


#FY 1972 


14,344,000.00 






14,344,000.00 


FY 1973 


15,571 ,000.00 






15,571 ,000.00 


#FY 197^+ 


7,443,633.23 


$ 0. 


30 


7,443,633.53 


FY 1965-78 (STO) 


4,282,700.00 


200,000. 


00 


4,482,700.00 


#FY 1975 


11.384,550.00 


-68. 


00 


11 ,384,482.00 


FY 1976 


10,456,000.00 






10,456,000.00 


FY 197T 


3,397,000.00 






3,397.000.00 


FY 1977 


6,911,182.80 


429,817. 


20 


7.341 ,000.00 


FY 1978 




15.457,763.19 
$16,087,512.69 


15,457,763.19 


SUBTOTAL 


$159,643,472.95 


$175,730,985.64 


ccflM ILct7\ 










FY 1964 


$ 3,400,000.00 






$ 3,400,000.00 


FY 1965 


7,494,526.42 






7,494,526.42 


FY 1966 


3,999,903.53 






3.999,903.53 


FY 1967 


3.985,091.00 


$ -2,898 


.00 


3,982,193.00 


FY 1968 


4,962,531.20 






4,962,531.20 


FY 1968 (STO) 


36,000.00 
$23,878,052.15 






36,000.00 


SUBTOTAL 


$ -2,898. 


,00 


$23,875,154.15 



^Includes San Marco. 



320 



TABLE LXXVIl Continued - SCOUT PROGRAM FY 1978 OBLIGATIONS, 

October 1 , 1979 



FISCAL YEAR FUNDS FY 1977 & PRIOR 

SAN MARCO 



FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 
FY 



1963 
1964 

1965 
1966 
1967 
1968 
1964 
1965 
1967 
1969 
1970 
1973 
1975 



Trust 
Trust 
Trust 
Trust 
Trust 
Trust 
Trust 



Fund 
Fund 
Fund 
Fund 
Fund 
Fund 
Fund 



SUBTOTAL 

ESRO IB 

FY 1970 
FY 1971 
FY 1975 

SUBTOTAL 

ESRO IV 



FY 
FY 
FY 
FY 
FY 



1970 
1971 
1972 
1973 
1976 



SUBTOTAL 
UK-X4 



FY 
FY 
FY 
FY 
FY 
FY 



1972 
1973 
1974 
1975 
1976 
1975 



(STO) 



FY 1978 



TOTAL 



SUBTOTAL 



$1,865,915.72 






$ 1,865,915.72 


337,733.13 






337,733.13 


500,000,00 






500,000.00 


350,000.00 






350,000.00 


100,000,00 






100,000.00 


70,000.00 






70,000,00 


200,000.00 






200,000.00 


480,465.00 






480,465.00 


29,672.84 






29,672.84 


48,009.06 






48,009.06 


250,000.00 






250,000.00 


1,262,647.24 






1 ,262,647.24 


653,600.00 






653,600.00 


$6,148,042.99 






$6,148,042.99 


$1,902,771.00 






$ 1,902,771.00 


350,000.00 






350,000.00 


210,656.00 






210,656.00 


$2,463,427.00 






$ 2,463,427.00 


$ 50,000.00 






$ 50,000.00 


1 ,500,000.00 


$ -26,691 


.72 


1,473,308.28 


800,000.00 






800,000.00 


331,834.00 






331,834.00 


911 .167.00 






911 ,167.00 


$3,593,001 .00 


$ -26.691 


.72 


$3,566,309.28 


$ 50,000.00 






$ 50,000.00 


1,345,373.00 


$ -23 


.02 


1,345,349.98 


1,695,785.79 


-36.93 


1,695,748.86 


679,618.66 


-77 


.32 


679,541.34 


-28.83 


28.83 





76,988.00 






76,988.00 


$3,847,736.62 


$ -108 


.44 


$3,847,628.18 



321 



1 


MBLt Lf 


.AVI 1 uontinued - SCOUT 


PROG 


RAM FY 1978 


OBLIGATIONS. 






October 


1, 1979 




FISCAL YEAR F 


■UNDS 


FY 1977 & PRIOR 




FY 1978 


TOTAL 


DELTA MOTORS 








FY 1964 
FY 1965 
FY 1966 




$ 430,000.00 
548,758.00 
488.157.00 






$ 430,000.00 
548,758.00 
488.157.00 


SUBTOTAL 




$1,466,915.00 






$1,466,915.00 


CONSTRUCTION 


OF FACILITIES 








FY i960 (STO) 
FY 1962 
FY 1977 


$1,200,000.00 

1,433,131.43 




^ 


83,202.00 


$1,200,000.00 

1,433,131.43 

83.202.00 


SUBTOTAL 




$2,633,131.43 


_i_ 


83,202.00 


$2,716,333.43 


'-NASA TOTAL 




$228,974,270.07 


$16,041,016.53 


$245,015,286.60 


REIMBURSABLE 


- INTERNATIONAL 








AEROS-B (483) 












FY 1974 
FY 1975 
FY 1976 
FY 1977 
FY 1978 
FY 1975 (STO) 


$2,640,000.00 

1,098,779.29 

24,617.17 

20,500.29 



45.275.00 


$ 


-92,049.52 



-81 .65 

609.88 

287.965.04 


$2,640,000.00 

1,006,729.77 

24,617.17 

20,418.64 

609.88 
333.240.04 


SUBTOTAL 




$3,829,171.75 


$ 


196,443.75 


$4,025,615.50 


ITALY 












FY 1977 
FY 1978 
FY 1977-78 


(STO) 


$ 183,363.00 




$ 


269,484.15 
210,000.00 


■ 

$ 183,363.00 
269,484.15 
210.000.00 


SUBTOTAL 




$ 183,363.00 


$ 


479,484.15 


$ 662,847.15 


UK-5 (483) 












FY 1974 
FY 1975 
FY 1976 
FY 1974-76 


(STO) 


$ 58,325.00 

65,000.00 

11,307.15 

737,956.00 






$ 58,325.00 
65,000.00 

11,307.15 
737,956.00 


SUBTOTAL 




$ 872,588.15 






$ 872,588.15 



i'Doss Not include suballotments received nor SRT funds. 



322 



TABLE LXXVII Continued - SCOUT PROGRAM FY 1978 OBLIGATIONS 



October 1 , 1979 
FISCAL YEAR FUNDS FY 197 7 & PRIOR FY 1978 



TOTAL 



REIMBURSABLE - 


INTERNATIONAL. Continued 






UK-6 (483) 








FY 1975 


$ 30,630.39 


$ 67,369.61 


$ 98.000.00 


FY 1976 


1,288.05 


1,071,889.05 


1.073.177.10 


FY 197T 


1,298.57 


-1,298.57 





FY 1977 


3,875.60 


137,443.86 


141.319.46 


FY 1978 





45,050.81 


45.050.81 


SUBTOTAL 


$ 37.092.61 


$1,320,454.76 


$1,357,547.37 


REIMB-INTERNAT' 


L TOTAL $4,922,215.51 


$1,996,382.66 


$6,918,598.17 


AIR FORCE 








*FY I960 


$ 5,603,061.78 




$ 5,603,061.78 


*FY 1961 


1,115,874.28 




1,115,874.28 


FY 1962 


10,273,856.95 




10,273.856.95 


FY 1963 


6,932,001.20 




6,932,001.20 


FY 1964 


977,381.00 




977,381.00 


FY 1965 


2,745,320.44 




2,745,320.44 


FY 1966 


2,025,847.58 




2,025.847.58 


FY 1967 


11 ,991,000.00 


$ -798,641.86 


11,192.358.14 


FY 1968 


7,463,076.00 


-582,013.89 


6,881 ,062.11 


FY 1967-8-9-C 


) (VAFB) 679,281.00 




679.281.00 


FY 1969 


484,533.71 




484,533.71 


FY 1970 


1,020,931 .00 




1,020,931 .00 


FY 1971 


308,400.74 


1,074,896.97 


1,383,297.71 


FY 1972 


602,508.00 


-0.23 


602,507.77 


FY 1973 


64,151.00 


-81 .98 


64,069.02 


FY 1974 


2.657.301.52 


4,860.527.57 


7,517,829.09 


FY 1975 


1,290,000.00 


-603,701.07 


686,298.93 


FY 1976 


1,655,493.49 


3,997,962.74 


5,653,456.23 


FY 197T 


11,534.61 




11,534.61 


FY 1977 


3,747.17 


1.803,809.63 


1,807,556.80 


FY 1978 




196.736.48 
$9,949,494.36 


196.736.48 


SUBTOTAL 


$57,905,301.47 


$67,854,795.83 


'•^09A Program. 







323 



TABLE LXXVII Concluded - SCOUT PROGRAM FY 1978 

October 1 , 1979 



OBLIGATIONS. 



FISCAL YEAR FUNDS 



AEC 

FY 1963 (AL) 
FY 1963 
FY 1974 

SUBTOTAL 

REIMBURSABLE TOTALS 

TOTAL 



FY 1977 & PR I OR 



NAVY 

FY 1961 
FY 1962 
FY 1965 
FY 1971 
FY 1975 
FY 1977 


$1,800,000.00 

7,900,000.00 

3,348.00 

2,600.00 

65,000.00 


SUBTOTAL 
REIMBURSABLE - DOD 


$9,770,948.00 



$ 26,563.60 
2,371,000.00 

220.000.00 

$2.617.563.60 

$70,293,813.07 

$304,237,660.65 



FY 1978 



$ 94.000.00 
$ 94,000.00 



$10,043,494.36 
$28,180,893.55 



TOTAL 



$1,800,000.00 

7,900,000.00 

3,348.00 

2,600.00 

65,000.00 

94.000.00 

$9,864,948.00 



$ 26,563.60 

2,371 ,000.00 

220.000.00 

$2.617.563.60 

$80,337.304.43 

$332,647,192.20 



324 



TABLE 


LXXVIII - SCOUT PROGRAM FY 1979 OBLIGATIONS. 




October 1 


. 1979 






FISCAL YEAR FUNDS 


FY 1978 & PRIOR 


FY 1979 




TOTAL 


DEVELOPMENTS (890) 








FY 1959 (STG) 


$ 3,810,488.00 






$ 3,810,488.00 


FY 1959 


3,365,593.25 






3,365.593.25 


FY I960 


2,978.043.04 






2,978,043.04 


FY 1961 


6,600,000.00 






6.600,000.00 


FY 1962 


2,911,217.42 






2,911,217.42 


FY 1963 


3,484,149.22 






3.484,149.22 


FY 1961 (STO) 


300,000.00 






300,000.00 


FY 1962 (STO) 


1,725,000.00 






1,725.000.00 


FY 1963 (STO) 


402,000.00 






402.000.00 


SUBTOTAL 


$25,576,490.93 






$25,576,490.93 


PRODUCTION (490) 










FY 1961 


$ 1,200,000.00 






$ 1,200.000.00 


FY 1962 


6,582,817.92 






6,582,817.92 


FY 1963 


8,054,000.00 






8,054,000.00 


FY 1964 


8,100,000.00 






8,100,000.00 


FY 1965 


5,688,300.00 






5,688,300.00 


FY 1966 


7,600,000.00 






7,600,000.00 


FY 1967 


5,399,602.00 






5,399,602.00 


FY 1968 


5,163,000.00 






5,163,000.00 


FY 1969 


12,490,988.00 






12,490,988.00 


#FY 1970 


13,034,634,00 


-942.90 


13.033,691.10 


#FY 1971 


12,540,065.00 






12,540,065.00 


#FY 1972 


14,344,000.00 






14,344,000.00 


FY 1973 


15,571,000.00 


-229. 


.52 


15,570,770.00 


#FY 1974 


7,443,633.53 


-268 


.30 


7,443,365.23 


FY 1965-79 (STO) 


4,482,700.00 


160.000 


.00 


4.642,700.00 


#FY 1975 


11,384,482.00 






11.384,482.00 


FY 1976 


10,456,000.00 






10,456,000.00 


FY 197T 


3,397,000.00 






3.397.000.00 


FY 1977 


7,341,000.00 






7,341,000.00 


FY 1978 


15.457,763.19 


642.236.81 


16,100,000.00 


FY 1979 




10,207.267.61 
$10,908,063.70 


10.207.267.61 


SUBTOTAL 


$175,730,985.64 


$186,639,049.34 


SEAM (497) 










FY 1964 


$ 3,400,000.00 






$ 3,400,000.00 


FY 1965 


7.494,526.42 






7,494,526.42 


FY 1966 


3,999,903.53 






3,999,903.53 


FY 1967 


3,982,193.00 






3,982.193.00 


FY 1968 


4.962,531.20 






4,962,531.20 


FY 1968 (STO) 


36.000.00 
$23,875,154.15 






36.000.00 


SUBTOTAL 


$23,875,154.15 


^Includes San Marco. 











325 



TABLE LXXVII I Conti 



nued - SCOUT PROGRAM 
October 1 , 1979 



FY 1979 OBLIGATIONS 



FISCAL YEAR FUNDS 



FY 1978 & PRIOR 



FY 1979 



TOTAL 



SAN MARCO 














FY 1963 






$1,865,915.72 






$1,865,915.72 


FY 1964 






337.733.13 






337,733.13 


FY 1965 






500,000.00 






500,000.00 


FY 1966 






350,000.00 






350,000.00 


FY 1967 






100,000.00 






100,000.00 


FY 1968 






70,000.00 






70,000.00 


FY 1964 


Trust 


Fund 


200,000.00 






200,000.00 


FY 1965 


Trust 


Fund 


480,465.00 






480,465.00 


FY 1967 


Trust 


Fund 


29,672.84 






29,672.84 


FY 1969 


Trust 


Fund 


48,009.06 






48,009.06 


FY 1970 


Trust 


Fund 


250,000.00 






250,000.00 


FY 1973 


Trust 


Fund 


1,262,647.24 






1,262,647.24 


FY 1975 


Trust 


Fund 


653,600.00 






653.600.00 


SUBTOTAL 






$6,148,042.99 






$6,148,042.99 


ESRO IB 














FY 1970 






$1,902,771.00 






$1,902,771.00 


FY 1971 






350,000.00 






350,000.00 


FY 1975 






210,656.00 






210,656.00 


SUBTOTAL 






$2,463,427.00 






$2,463,427.00 


ESRO IV 














FY 1970 






$ 50,000.00 






$ 50,000.00 


FY 1971 






1,473,308.28 


26,691 . 


.72 


1,500,000.00 


FY 1972 






800,000.00 






800,000.00 


FY 1973 






331,834.00 






331,834.00 


FY 1976 






911,167.00 
$3,566,309.28 






911.167.00 


SUBTOTAL 


$26,691. 


.72 


$3,593,001.00 


UK-X4 














FY 1972 






$ 50,000,00 






$ 50,000.00 


FY 1973 






1,345,349.98 


$ 23 


.02 


1.345,373.00 


FY 1974 






1,695,748.86 


37. 


.14 


1,695,786.00 


FY 1975 






679,541 .34 


1,055 


.66 


680,597.00 


FY 1975 


(STO) 




76.988.00 






76.977.00 



SUBTOTAL 



$3,847,628.18 



— r\^ 



$ 1, 1 ii..oz 



<;"? 84S 744 rin 



326 



TABLE LXXVIII 


Continued - SCOUT PROGRAM FY 1979 < 
October 1, 1979 


DBLIGATIONS 


FISCAL YEAR FUNDS 
DELTA MOTORS 




FY 1978 & PRIOR 


FY 1979 




TOTAL 








FY 1964 
FY 1965 
FY 1966 




$ 


430,000.00 
548,758.00 
488.157.00 




$ 


430,000.00 
548,758.00 
488.157.00 


SUBTOTAL 




$ 


1,466,915.00 




$ 


1,466.915.00 


CONSTRUCTION 


OF FACILITIES 








FY i960 (STO) 
FY 1962 
FY 1978 


$ 


1,200,000.00 

1.433,131.43 

83.202.00 




$ 


1.200,000.00 

1,433,131.43 

83,202.00 


SUBTOTAL 
-•-NASA TOTAL 




1 


2. 716.333.43 




i. 


2. 716. 333. 43 


$245,015,286.60 


$10,935,871.24 


$255,951,157.84 


REIMBURSABLE 


- INTERNATIONAL 








AEROS-B (483) 














FY 1974 
FY 1975 
FY 1976 
FY 1977 
FY 1978 
FY 1975 (STO) 

SUBTOTAL 




$2,640,000.00 

1.006,729.77 

24.617.17 

20,418.64 

609.88 

333.240.04 

$4,025,615.50 


$ 5,265.23 
227.79 




$2,640,000.00 
1,011.995.00 

24,617.17 

20,418.64 

837.67 

333.240.04 


$ 5,493.02 


$4,031,108.52 


ITALY 














FY 1977 
FY 1978 
FY 1977-78 

SUBTOTAL 


(STO) 




$ 183.363.00 
269,484.15 
210.000.00 

$ 662,847.15 


$ 206,662.00 




$ 183,363.00 
476,146.15 
210,000.00 


$ 206,662.00 


$ 869.509.15 


UK-5 (483) 














FY 1974 
FY 1975 
FY 1976 
FY 1974-76 


(STO) 




$ 58,325.00 

65,000.00 

11,307.15 

737,956.00 






$ 58,325.00 

•05.000. 00 

11.307.15 
737.956.00 


SUBTOTAL 






$ 872,588.15 
otments received 


nor SRT funds. 




$ ^72,588.15 


'-Does not inc 


Jude ; 


jubal 1 





327 



TABLE LXXVIII Continued - SCOUT PROGRAM FY 1979 OBLIGATIONS 

October 1 , 1979 



FISCAL YEAR FUNDS 


FY 1978 & PRIOR 
lONAL. Continued 


FY 1979 


TOTAL 


REIMBURSABLE - INTER NAT 






UK-6 Ci+83) 








FY 1975 


$ 98,000.00 




$ 98,000.00 


FY 1976 


1,073.177.10 


$1,219,376.21 


2,292.553.31 


FY 1977 


141,319.46 


-40.00 


141,279.46 


FY 1978 


45,050.81 


1,673,360.00 


1.718,410.81 


FY 1979 




114.266.32 
$3,006,962.53 


114.266.32 


SUBTOTAL 


$1,357,547.27 


$4,364,509.90 


REIMB-INTERNAT'L TOTAL 


$6,918,598.17 


$3,219,117.55 


$10,137,715.72 


AIR FORCE 








'•'FY i960 


$ 5,603,061.78 




$ 5.603,061.78 


■^fy 1961 


1,115,874.28 




1,115,874.28 


FY 1962 


10,273,856.95 




10,273.856.95 


FY 1963 


6,932,001.20 




6,932,001.20 


FY 1964 


977,381.00 




977,381.00 


FY 1965 


2,745,320.44 




2.745,320.44 


FY 1966 


2,025.847.58 




2,025,847.58 


FY 1967 


11,192,358.14 


796,520.07 


11,988,878.21 


FY 1968 


6,881,062.11 


575,265.03 


7,456,327.14 


FY 1967-8-9-0 (VAFB) 


679,281.00 




679,281.00 


FY 1969 


484,533.71 




484,533.71 


FY 1970 


1,020,931.00 




1,020.931.00 


FY 1971 


1,383,297.71 


230,057.57 


1,613,355.28 


FY 1972 


602,507.77 


-22,654.92 


579,852.85 


FY 1973 


64.069.02 


81.98 


64,151.00 


FY 1974 


7,517.829.09 


-113,991.17 


7.403,837.92 


FY 1975 


686,298.93 


530,155.00 


1,216,453.93 


FY 1976 


5,653,456.23 


-1,012,817.50 


4,640,638.73 


FY i97T 


11,534.61 




11,534.61 


FY 1977 


1,807,556.80 


481 ,850.98 


2,289,407.78 


FY 1978 


196,736.48 


4,980.513.48 


5,177,249.52 


FY 1979 




534.653.20 


534.653.20 


SUBTOTAL 


$67,854,795.83 


$6,979,633.28 


$74,834,429.11 


■>'^09A Program. 





328 



TABLE LXXVIII Concluded - SCOUT PROGRAM FY 1979 OBLIGATIONS 

October 1 , 1979 



FISCAL YEAR FUNDS 



FY 1978 & PRIOR 



FY 1979 



NAVY 








FY 1961 
FY 1962 
FY 1965 
FY 1971 
FY 1975 
FY 1978 




$1,800,000.00 

7,900,000.00 

3,3^8.00 

2,600.00 

65,000.00 

94,000.00 




SUBTOTAL 




$9,864,948.00 




REIMBURSABLE - 


DOD 






AEC 








FY 1963 (AL) 
FY 1963 
FY 196i+ 




$ 26,563.60 

2,371,000.00 

220.000.00 




SUBTOTAL 


OTAL 


$2,617,563.60 

$80,337,307.43 

$332,647,192.20 




REIMBURSABLE T 


$6,979,633.28 


TOTAL 


$21,134,622.07 



TOTAL 



$1 ,800,000.00 

7,900,000.00 

3,348.00 

2,600.00 

65,000.00 

94.000.00 

$9,864,948.00 



$ 26,563.60 

2,371,000.00 

220.000.00 

$2.617.563.60 

$87.316.940.71 

$353,781,814.27 



Tables LXXIX through XCII present the Scout Program Obligation by fiscal year for 
NASA funding. 



The summary of obligations noted is as follows: 
Phases prior to Vl 
Phase VI 
Phases Subsequent through 1979 



$68,600,297.55 
38,223,798.88 
79.459,747.30 



329 

TABLE LXXIX (a) - FY I96I NASA PRODUCTION (^^90) OBLIGATIONS 

PHASE II $ 994. 867.^+9 

PHASE III 205.132.51 

TOTAL $1,200,000.00 

TABLE LXXIX (b) - FY 1962 NASA PRODUCTION (^90) OBLIGATIONS 

PHASE II $1,320,697.75 

PHASE III 5,236,255-53 

PHASE IV 16,854.79 

SUBAUTHOR I ZAT I ON 9 ,009 -85 

TOTAL $6,582,817.92 

TABLE LXXIX (c) - FY 1963 NASA PRODUCTION (490) OBLIGATIONS 

PHASE II $ 616,349.56 

PHASE III 1 ,224,911.88 

PHASE IV 6,123,934.56 

PHASE V 88.804.00 

TOTAL $8,054,000.00 

TABLE LXXIX (d) - FY 1964 NASA PRODUCTION (490) OBLIGATIONS 

PHASE II $ 129.810.57 

PHASE III 6,444,839.53 

PHASE IV 1,484,215.90 

PHASE V 41 .134.00 

TOTAL $8,100,000.00 



TABLE LXXIX (e) 



TABLE LXXIX (f) 



PHASE VI 



JOB ORDER NO. 



E6I9IZ 



ORDER NO, 



NASI-7IO2 



330 

FY 1965 NASA PRODUCTION (490) OBLIGATIONS 
PHASE I I 
PHASE I I I 
PHASE IV 
PHASE V 
TOTAL 

FY 1966 NASA PRODUCTION (490) OBLIGATIONS 
PHASE IV 
PHASE V 
PHASE VI 
TOTAL 

ITEM DESCRIPTION 



TABLE UXIX (g) 



002 BE3A9 Motor 
TOTAL 

FY 1967 NASA PRODUCTION (490) OBLIGATIONS 
PHASE IV 
PHASE V 
PHASE VI 
TOTAL 



$ 2,500.00 

1 ,508,156.68 

3,463,489.68 

714.153-64 

$5,688,300.00 



$5,492,396.68 

2,091,821.32 

15.782.00 

$7,600,000.00 



OBLIGATION 
$ 15.782.00 
$ 15,782.00 



$ 784,837.70 

4,1^78,212.30 

136.552.00 

$5,399,602.00 



PHASE VI 










JOB ORDER NO. 


ORDER NO. 


ITEM 


DESCRIPTION 


OBLIGATION 


E6OOOW 
E6I9IZ 


L5009 
NASI -7102 


002 
004 


BE3A9 Casting Powder 
BE3 Motors 


$ 2,334.00 
134.218.00 



TOTAL 



$ 136,552.00 



331 



TABLE LXXX - FY 1968 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV 
PHASE V 
PHASE VI 
TOTAL 



PHASE VI 








JOB ORDER NO. 


ORDER NO. 


ITEM 


DESCRIPTION 


E6000H 


NASI -7256-6 


El 9 


Instrumented E-Section 


E6000H 


NASI -71 99-1 5 (R6) 


686 


MODS-SBASI 


E6000M 


NASI -10000-25 


D39 


Battery Cells 


E6000W 


L28596 


002 


Tools for Connectors 


E6000W 


L34648 


002 


Metal Finishing Supplies 


E6000Z 


L9706 


002 


Third-Stage Casting Powder 


E6180Z 


NAS1-7199 


588 


Second-Stage Motors, S-180 


E6181Y 


NASI -71 99 


549 


S-181 Hardware 


E6183Y 


NAS1-71 99-14 


G83 


S-183 S-Band 


E6183Z 


NASI -7199 


595 


S-183 Second-Stage Motor 


E6184Z 


NAS1-7199 


689 


S-184 Second-Stage Motor 


E6187Z 


NASI -71 99 


690 


S-187 Second-Stage Motor 


E6190Y 


NASI -71 99 


560 


A-66 Heat Shield 



Shipping 



TOTAL 



$1,181,308-39 
^.971,987-64 
1.046.703.97 

$5,200,000.00 

OBLIGATION 

$ 74,600.00 

30,948.00 

1 ,200.00 

65.08 

20.00 

59,915.39 
96,215.00 
420.358.00 
52,281 .00 
96,215.00 
96,215.00 
96,215.00 
22,278.00 
178.50 

$1,0^46,703.97 



TABLE LXXX I - FY 1969 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV 
PHASE V 
PHASE VI 
PHASE V I I 
SUBAUTHORIZATIONS V 



$ 671 »855 -V 
4,602,216.76 

4,105,466.7^ 
3,294,373.5 6 

24,775.47 



TOTAL 



$12,698,688.00 



332 



TABLE LXXXI Continued - FY 1969 NASA PRODUCTION (490) OBLIGATIONS 



PHASE VI 



JOB ORDER NO. 


ORDER NO. 


ITEM 


DESCRIPTION 


OBLIGATION 


E6000R 


NAS1-6020-19 


541 


Revise QCEPS $ 


81 ,504.00 


E6000R 


NASI -71 99-1 9 


666 


Change GFE 


-4,487.00 


E6000R 


NASI -71 99-25 


672 


FW4S Leak Test 


5,000.00 


E6000W 


L-28102 


002 


Product Improvement 


150.06 


E6000W 


L- 281 03 


002 


Product Improvement 


120.80 


E6000W 


L-28596 


004 


Product Improvement 


68.07 


E6000W 


L-29500 


002 


Product Improvement 


263.15 


E6000W 


L- 299 19 


002 


Product Improvement 


92.76 


E6000R 


NASI -71 02-3 


006 


BE3A9 Igniter Mods. 


54,200.00 


E6000R 


NASI -71 02-5 


008 


BE3A9 Text Mods. 


1,450.00 


E6000W 


NASI -7256 


002 


Product Improvement 


1 ,000.00 


E6000Y 


NASI -7256-33(031) 


E38 


Phase VI Vehicle Procurement 


5,798.00 


E6180Y 


NASI -71 99 


596 


CAS-A Vehicle Procurement 


22,278.00 


E6180Y 


NASI-7I99 


692 


CAS-A Vehicle Procurement 


420,358.00 


E6180Z 


NASI -71 99 


600 


CAS-A Motor Procurement 


74,188.00 


E6180Z 


NASI -10000 


954 


CAS-A Motor Procurement 


1,656.40 


E6181W 


NASI -10000 


G20 


AEROS-A Award Incentive 


105,286.00 


E6181Y 


NAS1-7256-33(C31) 


354 


E-Section for S-I8I (AEROS-A) 


7,180.00 


E6181Z 


NASI -71 99-1 


601 


AEROS-A Motor Procurement 


74,188.00 


E6181Z 


NASI -71 99-2 


F28 


AEROS-A Motor Procurement 


1,656.40 


E6181Z 


NASI -71 99 


599 


AEROS-A Motor Procurement 


96,215.00 


E6183G 


NASI -10000 


A04 


UK-4 Standardization 


65,764.00 


E6183Y 


NASI -71 99-4 


g87 


UK-4 Vehicle Procurement 


1,382.00 


E6183Y 


NASI -71 99-1 4 


G88 


UK-4 Vehicle Procurement 


52,281 .00 


E6183Y 


NASI -71 99 


551 


UK-4 Vehicle Procurement 


420,358.00 


E6183Y 


NASI-7I99 


673 


UK-4 Vehicle Procurement 


22,278.00 


E6183Z 


N,!\S1-7199 


662 


UK-4 Motor Procurement 


122,720.00 


E6183Z 


NAS1-7199-1 


671 


UK-4 Motor Procurement 


74,187.00 


E6183Z 


NASI -10000 


928 


UK-4 Motor Procurement 


1,656.00 


E6184Y 


NASI -71 99 


553 


MTS-A Vehicle Procurement 


420,258.00 


E6184Z 


NASI-7I99-I 


603 


MTS-A Motor Procurement 


74,187.00 


E6l8itZ 


NASI -9258 


f82 


MTS-A Motor Procurement 


126,792.00 


E6l8itZ 


NASI -10000-2 


936 


MTS-A Motor Procurement 


1,656.00 


E6187B 


NASI-I25OO 


H51 


Mission Integration, UK-5 


4,304.00 


E6187Z 


NASI -71 99-1 


659 


UK-5 Motor Procurement 


74,188.00 


E6187Z 


NASI -71 99-4 


663 


UK-5 Motor Procurement 


122,720.00 


E6187Z 


NASI -10000-23 


827 


UK-5 Initiators 


968.00 


E6187Z 


NASI -10000-23 


829 


UK-5 Initiators 


770.00 


E6187Z 


NASI -10000-23 


833 


UK-5 Initiators 


770.00 


E6189A 


NASI -12500 


952 


ANS-A Program Management 


246,447.00 


E6189Y 


NASI -71 99-1 4 


CI3 


ANS-A Vehicle Procurement 


52,281 .00 


E6189Y 


NASI -71 99 


558 


ANS-A Vehicle Procurement 


420,358.00 


E6189Y 


NAS1-7199-4 


E23 


ANS-A Vehicle Procurement 


1,382.00 


E6189Z 


NASI-7I99-I 


598 


ANS-A Motor Procurement 


74,188.00 


E6189Z 


NASI-7I99 


602 


ANS-A Motor Procurement 


96,215.00 



333 



TABLE LXXXI Concluded - FY 1969 NASA PRODUCTION (^90) OBLIGATIONS 



PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6190Y 

E6190Z 

E6190Z 

E6I9IG 

E6191J(R1230) 

E6191J(R1230) 



ITEM DESCRIPTION 



TOTAL 



OBLIGATION 



NASI- 


-7199 


559 


SM-C2 Vehicle Procurement 


$ 420,358.00 


NASI' 


-7199 


597 


SM-C2 Motor Procurement 


96,215.00 


NASI' 


-7199-1 


604 


SM-C2 Motor Procurement 


74,188.00 


NASI' 


-10000 


AI7 


Hawkeye Standardization 


54,538.00 


NASI- 


-6868 


004 


Misc. 5th Stage Components 


25,882.05 


NASI- 


-6868 


005 


Contract Adjustment 
Stock Issues 
Shipping 


-3,638.00 

276.83 

11,270.82 



$ 4,105,466.74 



TABLE LXXXI I 



FY 1970 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV $ 248,740.23 

PHASE V 8,685,276.36 

PHASE VI 2,631,067-77 

PHASE VII 1,451,941.88 

SUBAUTHORIZATION V 134,664.86 



PHASE VI 



JOB ORDER NO. ORDER NO. 



TOTAL 



ITEM DESCRIPTION 



$13,l5f,691.10 



AEA101 


NASI -10900 


003 


E6OOOE 


NASI -10000 


D47 


E6000H(RAS174) 


NASl-6935-5(Tl3) 




E60000 


NASl-71 99-18 


CIS 


E6OOOO 


NASI -71 99-22 


CI9 


E6OOOO 


NASI -71 99-28 


C20 


E6OOOR 


L-9695 


002 


E6OOOR 


NASI -6935-41 


029 


E6000R 


NASI -6935-41 -4 


029 


tbUUUR 


NASI -71 99-5 


bl / 


E6OOOR 


NASI -7199-8 


C21 


E6OOOR 


NASI -71 99-24 


621 


E6OOOR 


NASI -9258 


F80 


E6OOOU 


NASI -91 54 


002 


E6OOOV 


NASI -10000-1 6 


D65 



IMS 

Phase VI Systems Engineering 

Design S-Band T/M 

Phase VI Repair Algol Dollies 

Phase VI Algol Dolly Tires 

Phase VI Algol Storage at AEDC 

Firing BE3A9 Motor at AEDC 

Regulator 

Regulator 

500 Pound PCM/Vaive Assembly 

Inspect Castor Nozzles 

Mods for SBASI 

Design and Develop Algol III 

Flight Tape Recorder 

Phase VI Tooling Maintenance 



OBLIGATION 

i 1.45 

19,896.00 

88 073.00 

13^450.00 

277.00 

24,000.00 

25,200.00 

32,939.00 

61 ,420.00 

6,690.00 

7,025.00 

11 ,056.00 

1 ,050,000.00 

753.00 

65,262.00 



33k 



TABLE LXXXII Continued - FY 1970 NASA PRODUCTION (^90) OBLIGATIONS 



PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6000Y 


NASI 


-6935-41-2 


025 


E6000Y 


NASI 


-7199-23 


CIO 


E6000Z 


NASI 


-7199-4 


C11 


E6000Z 


NASI 


-7199 


C12 


E6000Z 


NASI 


-7256-4(C3) 


E20 


E6100H(RAS159) 


NASI 


-6935-4(Tl1) 




E6100M(RAS1^0) 


NASI 


-6935-9 (Til) 




E6180B 


NASI 


-7256 


708 


E6180H 


NASI 


-7256 


709 


E6180H 


NASI 


-7256-28 


710 


E6180R(RAS140) 


NASI 


-6935 (Til) 




E6180T 


NASI 


-10000 


F22 


E6180Y 


NASI 


-7256-3 


707 


E6180Y 


NASI 


-6935 (Til) 




E6180Z 


NASI 


-5610 


131 


E6180Z 


NASI 


-7199-4 


622 


E6181B 


NASI 


-7256 


711 


E6181H 


NASI 


-6935-7(T4l) 


024 


E6181Y 


NASI 


-10000 


G27 


E6181Y 


NASI 


-10000-20 


F26 


E6181Z 


NASI 


-10000-6 


F27 


E6181Z 


NASI 


-7199-16 


623 


E6183B 


NASI 


-7256 


712 


E6183R(RAS140) 


NASI 


-6935 (Til) 




E6183T 


NASI 


-10000 


F32 


E6183Y(RAS140) 


NASI 


-6935 (Til) 




E6193Z 


NASI 


-5610 


130 


E618'+Y 


NASI 


-10000 


G60 


E6184Y 


NASI 


-7199-14 


693 


E6184Z 


NASI 


-7199-16 


678 


E6184Z 


NASI 


-10000-6 


G08 


E6187T 


NASI 


-10000 


C44 


E6187Y 


NASI 


-6935-5(C4l) 


023 


E6187Y 


NASI 


-7199-14 


A01 


E6190T 


NASI 


-10000 


C21 


E6190Y 


NASI 


-10000 


C02 


E6190Y 


NASI 


-7199-14 


CI5 


E6190Z 


NASI 


-7199-16 




E6190Z 


NASI 


-9258 




E6191J 


NASI 


-5610-7 


C-3 


E6191Y 


NASI 


-7199 


CI 7 


E6191Z 


NASI 


-7199-16 


624 



ITEM DESCRIPTION OBLIGATION 



42-Inch Heat Shield $ 5,668.00 

Vehicle SBASI , Harness 864.00 

Phase VI 1st Stage Motor 122,720.00 

Phase VI 2nd Stage Motor 6,414.00 

Phase VI Initiators 76,512.00 

P/L Separation Timer Mods. 33,255.00 

Final Cost Adjustment -12,357.00 

CAS-A Mission Integration 10,479-00 

CAS-A Vehicle Processing 28,211.00 

CAS-A Vehicle Ignition System 405.00 

CAS-A Test E-Section #25 8,930.00 

CAS-A Production Support 811.00 
CAS-A Cork Installation on Base A 1,003.00 

CAS-A E-Section #36 8,930.00 

CAS-A 4th Stage Motor 33,070.00 

CAS-A 1st Stage Motor #15 122,720.00 

AEROS-A Mission Integration 10,479.00 

AEROS-A Processing 65O.8O 

AEROS-A Jet Vane & Fin Tips 16,116.00 

AEROS-A Vehicle Procurement 6,700.00 

AEROS-A 1st Stage Motor 28,367-00 

AEROS-A 4th Stage Motor 75,437-00 

UK-4 Mission Integration 20,960.00 

UK-4 Test E-Section #27 8,930.00 

UK-4 Production Support 447.00 

UK-4 Test E-Section #31 8,930.00 

4th Stage Motor #12 33,070.00 
MTS Fourth-Stage ignition & T/M 10,258.63 

MTS S-Band 52,281 .00 

MTS 4th Stage Motor 75,437-00 

MTS 1st Stage Motor 28,367.00 

UK-5 Production Support 1,221.00 

UK-5 Vehicle 65O.OO 

UK-5 S-Band 52,282.00 

SM-C2 Production Support 1,290.00 

SM-C2 Jet Vane and Fins 16,116.00 

SM-C2 S-Band 52,282.00 

SM-C2 Fourth-Stage Motor 75,437.00 

SM-C2 First-Stage Motor 126,792.00 

Hawkeye 5th Stage Motor 38,750.00 

Hawkeye S-Band 52,282.00 

Hawkeye 4th Stage Motor 75,437-00 

Stock Issues 8,022.97 

Shipping 102,638.35 

DIRECT DCASO 118,000.00 



TOTAL 



$2,631,067-77 



TABLE LXXXI II - 



335 

FY 1971 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV $ 315.937.95 

PHASE V 2,8Sif.i;32.32 

PHASE VI 6,631,575^1 

PHASE VII 3,213,3^+8.35 

SUBAUTHORIZATION V 123,769.97 

TOTAL $13,199,064.00 



PHASE VI 



JOB ORDER NO. ORDER NO. 



ITEM DESCRIPTION 



(AEA101 
E6000B 
E6OOOD 
E6000E 
E6OOOG 
E6OOOM 
E6OOOP 
E6OOOP 

E6000R(RAS173) 

E6OOOR 

E6OOOR 

E6000R 

E6000R 

E6OOOS 

E6OOOV 

E6OOOW 

E6OOOZ 

E6OOOZ 

E6OOOZ 

E6OOOZ 

E6OOOR 

r- C.-\ Qf\w- 

co I out 

E6I8OF 
E6I8OH 
E6I8OM 
E6I8OM 

E6180N 
E6I8OY 
E6181E 
E6181F 
E6181H 
E6181J 
E6181M 



)NAS1-10900 
NASI -10000 
NASI -10000 
NASI -10000 
NASI -10000 
NASI-I25OO 
NASI -10000 
NASI -6090 
NASI -6935-6 (T42) 
NASI -6935- 7 (T42) 

NASI -7258-27(027) 

NASI -9258 

NASI -10000 

NASI -10000 

NASI-I25OO 

NASI -6935-9 (C41) 

NASI -9258-7 

NASI -9258-3 

NASI -10000-9 

NASI -10000-32(021) 

NAS1-10482-Z 

NASI -10000 

NASI -10000 

NASI -10000 

NASI -10000 

NASI -10000-23 

NASI -10000 

NASI -10000-9 (CI 1) 

NASI -10000 

NASI -10000 

NASI -10000 

NASI -10000-32(020) 

NASI -10000 



032 
DO5 
DOS 
D54 
E90 
H61 
D02 
294 



E34 

F83 

D04 

681 

H60 

028 

F73 

F74 

C64 

C65 

005 

794 

G22 

F21 

A32 

F23 

F25 

657 

G18 

D48 

G24 

669 

A33 



IMS 



$ 



Phase VI Mission Integration 

Phase VI Data Analysis 

Phase VI Systems Engineering 

Phase VI Standardization 

Spares 

Phase VI LTV Support 

Computer Programer 

Modified Jet Vane Test 

Modified Jet Vane Test 

T/M Signal Cond . Unit 

Design and Develop Algol III 

P/L Environmental Control, WFC 

BE3A9 Motor Shelf Life Ext. 

Phase VI Tooling Maintenance 

Regulator 

1st Stage Test Motor #5 

Algol Case Test 

Ablative Cork 

Ultrasonic Standards for Algol I 

Technical Support, 2nd Stage 

CAS-A Systems Engineering 

CAS-A Rel iabi I i ty 

CAS-A Vehicle Processing 

CAS-A Spares 

CAS-A Spares 

CAS-A Launch Site Services 

CAS-A 4th Stage S-BanH 

AEROS-A Systems Engineering 

AEROS-A Rel iabil ity 

AEROS-A Vehicle Processing 

AEROS-A Protective Heat Shield 

AEROS-A Spares 



OBLIGATION 

50,811 .94 

139,527.00 

24,875.00 

9,422.71 

183,296.00 

137,315.00 

282,427.00 

31 ,000.00 

25,331.00 

-873.00 

1 ,607.00 

1,244,635.00 

2,635.00 

47,900.00 

52,625.00 

46,438.00 

126,792.00 

7,653.00 

2 , 740 . 00 

II 6,341.00 

23,684.00 

184,378.00 

154,385.00 

132,386.00 

13,708.00 

30,000.00 

393,228.00 

3^431 ,00 

196,'l69.00 

192,302.00 

166,860.00 

2,568.00 

30,392.00 



336 



TABLE LXXXIII Continued - FY 1971 NASA PRODUCTION (490) OBLIGATIONS 



PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



ITEM DESCRIPTION 



E6181M 
E6181N 
E6181N 
E6181Y 
E6181T 
E6181Y 
E6181Z 
E6183H 
E6183J 
E6183M 
E6183M 
E6183N 
E6184B 
E6184H 
E6184M 
E6184N 
E6184N 
E6l8itW 
E6184Y 
E6184Y 
E6184Z 
E6l8i|Z 
E6187M 
E6187M 
E6187T 
E6187T 
E6187Y 
E6187Z 
E6187Z 
E6189D 
E6189Y 
E6189Y 
E6189Y 
E6189Y 
E6189Z 
E6189Z 
E6189Z 
E6190H 
E6190M 
E6190T 
E6190Z 
E6I9OZ 
E6I9IT 
E6191Y 
E6I9IY 



NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 



-lOOOQ. 

-10000 

-10000 

-10000 

-10000 

-6935 

-9258 

-10000 

-10000 

-10000 

-10000 

-10000 

-10000 

-10000 

-lOOOO 

-10000 

-10000 

-10000 

-6935 

-10000 
-10000 

-10000 

-10000 
-10000 
-10000 
-10000 

-6935- 
-10000 
-11400 

-12500 

-10000 
-10000 
-6935- 
-10000 

-9258- 

-10000 
-11400 

-10000 
-10000 

-10000 

-9258 

-10000 

-10000 
-6935 

-10000 



23 
•n 

■15 

2(t41) 
7 

-9(C14) 

■23 
■11 



23 



2(C41) 

16(C15) 
-16(C16) 

-23 
15 

21 
2(C41) 
2 



15 

21 
2(t41) 
-3 
7 
-2 



-15 

2 

15 
2(C41) 

3 



F31 

A71 

G71 

054 

G26 

009 

F81 

G16 

F34 

A34 

302 

F36 

704 

G32 

A35 

F40 

G10 

G02 

012 

G33 

070 

665 

A40 

C46 

C43 

073 

010 

C45 

E02 

261 

056 

074 

015 

C67 

F75 

040 

EO3 

C80 

A41 

059 

F76 

037 

056 

014 

C11 



OBLIGATION 

AEROS-A Spares $ 27,lf92.00 

AEROS-A Launch Site Services 7,011.00 

AEROS-A Launch Site Services 386,217.00 

4th Stage Ignition and T/M 28,516.00 

AEROS-A Production Support 844.00 

AEROS-A Heat Shield #504 32,939-00 

AEROS-A 1st Stage Motor 126,792.00 

UK-4 Vehicle Processing 153,604.00 

UK-4 Mission Heat Shield Mod. 532.00 

UK-4 Spares 44,325-00 

UK-4 Spares 27,492.00 

UK-4 Launch Site Services 7,011.00 

MTS-A Mission Integration 22,027.00 

MTS-A Vehicle Processing 154,018.00 

MTS-A Spares 26,651 -00 

MTS-A Launch Site Services 216,273-36 

MTS-A Launch Site Services 166,324.53 

MTS-A Award Incentive 105,286.00 

MTS-A Heat Shield 402 31,451-00 

MTS-A Jet Vanes and Fin Tips 16,116.00 

MTS-A X-ray X259 HIB303 Motor 4,028.00 

MTS-A Inspect Castor II Motor 2,240.00 

UK-5 Spares 46,711 .00 

UK-5 Spares 22,000.00 
UK-5 Fourth-Stage Ignition & T/M 28,516.00 

UK-5 E-Section 6,745-00 

UK-5 Heat Shield 505 32,939-00 

UK-5 3rd Stage Motor 1,656.40 

UK-5 4th Stage Motor 34,501 .00 

ANS-A Data Analysis 11,590.00 

ANS-A 4th Stage Ignition & T/M 28,516.00 

ANS-A Production E-Section 6,745-00 

ANS-A Heat Shield 406 31,451.00 

ANS-A Jet Vanes and Fin Tips 13,143-00 

ANS-A Motor, First Stage 126,792-00 

ANS-A 3rd Stage Igniters 1,656-40 

ANS-A 4th Stage Motor 34,501 -00 

SM-C2 Vehicle Processing 124,353-00 

SM-C2 Spares 49,849-00 
SM-C2 4th Stage Igniters and T/M 28,516-00 

SM-C2 1st Stage Motor 126,792.00 

SM-C2 3rd Stage Initiator 1,656.40 
Hawkeye 4th Stage Igniter & T/M 28,516.00 

Hawkeye Heat Shield 405 31,451-00 

HawkeyeJet Vanes and Fin Tips 16,116.00 



337 



TABLE LXXXI I I Concluded 
PHASE VI Continued 
JOB ORDER NO. ORDER NO. 



FY 1971 NASA PRODUCTION (490) OBLIGATIONS 



ITEM DESCRIPTION 



E6191Z 


NASI -7256-27 


E29 Services for BE3A9 Motor 


$ 


2,834.00 


E6191Z 


NASI -9258- 7 


F77 Hawkeye Motor, First Stage 
Stock Issues 
Shipping 
DIRECT - DCASO 




126,792.00 

7,142.94 

64,914.73 

112,000.00 



TOTAL 



$ 6,681,575.41 



TABLE LXXXIV 



FY 1972 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV $ 308,440.43 

PHASE V 2,108,716.82 

PHASE VI 7,496,774.65 

PHASE VII 5,063,172.85 

SUBAUTHORIZATION (Phase Vl)^^^ 122.895.25 

TOTAL $15,100,000.00 



PHASE VI 



JOB ORDER NO. ORDER NO. 



E6OOOE 

E6OOOF 

E6OOOG 

E6OOOG 

E6OOOH 

E6OOOO 

E6OOOO 

E6OOOO 

E6OOOR 

E6OOOV 

E6OOOW 

E6000R(RAS183) 

E6OOOZ 

E6OOOZ 

E6180A 

E6180B 

E6180C 

E6180D 

E6I8OG 



NASI -10000 
NAS1-10000 
NASI -1 0000- 
NASl -10000- 
NAS1 -10000- 
L-55235 
L- 71 779 
NASI -1 0000- 
NAS1 -10000- 
NAS1 -6020-1 
NASI -1 0000- 
NAS1 -10500- 
L-55255 

L-55255 
NASI -10000 
NASI -10000 
NASI -10000 
NASI -10000 
NASI -10000 



13(R25) 
13(R32) 
13(R24) 



13(R17) 

13(R23) 

5(H) 

13(R79) 

01 



ITEM DESCRIPTION 



D53 

D21 

D29 

D31 

D12 

026 

002 

D10 

D11 

E02 

D37 

008 

020 

021 

947 

861 

871 

777 

A99 



$ 



Phase VI Systems Engineering 

Phase VI Rel iabi 1 i ty 

Phase VI Tunnel Tab Test Tooling 

Phase VI Wiring DBF at VAFB 

BE3A9 Motor Flight Preparation 

Phase VI G.S.E. 

Phase VI G.S.E. 

Mod. VEGA Beacons 

Phase VI GFE G.S.E. Kits, VAFB 

Phase VI Tooling Maintenance 

Hardware, Altair-IN XLDB 

P/L Separation Ignition Timers 

Third-Stage Propel lant 

Third-Stage Propel lant 

CAS-A Program Management 

CAS-A Mission Integration 

CAS-A Pref light Planning 

CAS-A Data Analysis 

CAS-A Standardization 



OBLIGATION 

186,915.37 

461,478.00 

44,560.00 

6,773.00 

355.00 

129.13 

54.20 

8,464.00 

8,140.00 

53,002.00 

41,075.00 

226,820.00 

23 242. °1 

4,'652.00 

318,938.00 

6,424.00 

17,271 .00 

51,317.00 

56,680.00 



v3/$50,000 in Phase V, 



338 



TABLE LXXXIV Continued 
PHASE VI Continued 



JOB ORDER NO. 


ORDER NO. 


ITEM 


E6180V 


NASI -10000 


Flk 


E6181A 


NASI -10000 


9if8 


E6181B 


NASI -10000 


862 


E6181C 


NASI -10000 


872 


E6181D 


NASI -10000 


785 


E6181G 


NASI -10000 


AO3 


E6181H 


NAS1-10000(R30) 


A82 


E6181H 


NASI -10000-1 3 (R30) 


G25 


E6181T 


NASI -7256 


Ekk 


E6181V 


NASI -7256 


E45 


E6181V 


NASI -10000 


208 


E6183B 


NASI -10000 


816 


E6183C 


NASI -10000 


873 


E6183D 


NAS1-10000 


786 


E6183E 


NAS1-10000 


d49 


E6183N 


NASI -10000 


A57 


E6183V 


NASI -10000 


F35 


E6l8i+A 


NASI -10000 


950 


E6184C 


NASI -10000 


874 


E6l8itD 


NASI -10000 


787 


E6184E 


NASI -10000 


D50 


E6184G 


NASI -10000 


A06 


E6184/ 


NASI -10000 


G34 


E6184V 


NASI -10000 


210 


E6187A 


NASI -10000 


834 


E6187C 


NASI -10000 


835 


E6187E 


NASI -10000 


836 


E6187G 


NASI -10000 


842 


E6187H 


NASI -10000 


840 


E6I870 


NAS1-10000(R58) 


A85 


E6187V 


NASI -10000 


845 


E6187Y 


NASI -7199 


543 


E61 89A 


NASI-I25OO 


957 


E6189B 


NASI -10000 


818 


E6189D 


NASI -12500 


260 


E6189E 


NASI -10000 


C22 


E6189F 


NASI -10000 


C20 


E6189G 


NASI -10000 


C70 


E6189H 


NASI -10000 


C68 


E6189M 


NASI -12500 




E6I9OA 


NASI -10000 


847 


E619OB 


NASI -10000 


819 


E6I9OC 


NASI -10000 


875 


E619OE 


NASI -10000 


C07 


E6I9OG 


NASI -10000 


906 


E6I9OV 


NASI -7256 


E27 



FY 1972 NASA PRODUCTION (490) OBLIGATIONS 



ITEM DESCRIPTION OBLIGATION 



CAS-A Tool ing Maintenance $ 65,262.00 

AEROS-A Program Management 318,938.00 

AEROS-A Mission Integration 9,425.00 

AEROS-A Pref light Planning 17,605.00 

AEROS-A Data Analysis 59,539.00 

AEROS-A Standardization 71,441.00 

Vehicle Reprocessing 52,700.00 

Vehicle Reprocessing 42,672.00 

AEROS-A Production Support 26,161.00 

AEROS-A Tooling Maintenance 31,003.00 

AEROS-A Tooling Maintenance 65,262.00 

UK-4 Mission Integration 2,829-00 

UK-4 Pref light Planning 27,562.00 

UK-4 Data Analysis 42,087-00 

UK-4 Systems Engineering 179,122.00 

UK-4 Launch Site Services 386,217-00 

UK-4 Tooling Maintenance 65,262.00 

MTS-A Program Management 318,938.00 

MTS-A Pref light Planning 23,656.00 

MTS-A Data Analysis 52,227.00 

MTS-A Systems Engineering 209,562.00 

MTS-A Standardization 76,112.00 
MTS-A Fourth-Stg. Ignition & T/M 18,257-37 

MTS-A Tooling Maintenance 65,262.00 

UK-5 Program Management 318,938.00 

UK-5 Pref light Planning 3,114.00 

UK-5 Systems Engineering 207,331-00 

UK-5 Standardization 76,121.00 

UK-5 Vehicle Processing 177,800.00 

UK-5 4th Stage Tip Off Rocket 1,786.00 

UK-5 Tooling Maintenance 65,262.00 

Vehicle Procurement, UK-5 420,358.00 

ANS-A Program Management 163,809-00 

ANS-A Mission Integration 8,123.00 

ANS-A Data Analysis 3,398.00 

ANS-A Systems Engineering 1,889.00 

ANS-A Rel lability 1,890.00 

ANS-A Standardization 694.00 

ANS-A Vehicle Processing 1,6l8.00 

Spares 37,079.00 

SM-C2 Program Management 318,938.00 

SM-C2 Mission Integration 4,097.00 

SM-C2 Pref light Planning 3,221.00 

SM-C2 Systems Engineering 145,013.00 

SM-C2 Standardization 53,240.00 

SM-C2 Tooling Maintenance 31,004.00 



339 



TABLE LXXXIV Concluded - FY 1972 NASA PRODUCTION (^90) OBLIGATIONS 



PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6190V 


NASI -10000 


COi^ 


E6191A 


NASI -10000 


8it8 


E6191B 


NASl-10000 


15h 


E6191E 


NASI -10000 


C18 


E6191H 


NASl-10000 


CIO 


E6191J 


NAS1-10000(r83) 


Z\k 


E6191J 


NAS1-10000(R93) 


CI5 


E6191T 


NASI -7256 


E28 


E6191T 


NASl-10000 


C12 


E6191V 


NASI -7256 


E30 


E6191V 


NASl-10000 


CI 7 


e6191R(RAS196) 


NASI -10500-03 


009 


e6191R(RAS184) 


NASI -10500-03 


010 


E6191R(RAS190) 


NASI -10500-03-2 


Oil 



ITEM DESCRIPTION 



SM-C2 Tooling Maintenance 
Hawkeye Program Management 
Hawkeye Mission Integration 
Hawkeye Systems Engineering 
Hawkeye Vehicle Processing 
Hawkeye GSE for ACS 5th Stage 
Hawkeye Spares for ACS 
Hawkeye Production Support 
Hawkeye Production Support 
Hawkeye Tooling Maintenance 
Hawkeye Tooling Maintenance 
Attitude Correction System 
Attitude Correction System 
Attitude Correction System 
Stock Issues 
Sh ipping 

Suballowment - Wallops 
Subal lotment - WTR 
SS DIRECT - DCASO 

IMS (Hqs.) 

TOTAL 



OBL I GAT I ON 



65 

159 

32 

128 

68 

84 

46 

26 

1 

31 

32 
140 
148 

-2 
607 

15 
(23 
(49 
138 

21 



,262.00 
,488.00 
,206.00 
,405.00 
,414.00 
,392.00 
,541 .00 
,160.00 
,490.00 
,004.00 
,610.00 
,000.00 
,500.00 
,227.00 
,505.48 
,909.19 
,225.86) 

,669.39) 

,000.00 

,000.00 



TABLE LXXXV - FY 1973 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV 
PHASE V 
PHASE VI 
PHASE VI I 
SUBAUTHORIZATION (Phase VI) 

TOTAL 



PHASE VI 



JOB ORDER NO. ORDER NO. 



ITEM DESCRIPTION 



E6OOOF 
E6OOOG 
E6OOOG 



NASI -10000-1 3 (R45) 
NASI -1 0000-13 (R57) 
NASI -10000-1 3 (R65) 



DI7 HE Propel lant Altair I I I 
Inspection of X259 HIB307 
D27 Back-up Air at VAFB 



$ 7,496,774.65 

$ 437,884.65 
795,410.80 

3,342,236.31 
10, 787,301.07 

336,937.65 
$15,699,770.48 

OBLIGATION 

$ 1,495.00 

18,828.00 

8,879.00 



3^0 



TABLE LXXXV Continued - FY 1973 NASA PRODUCTION (^90) OBLIGATIONS 



PHASE VI Continued 



JOB ORDER NO. 


ORDER NO. 


ITEM 


E6000G 


NASI -10000-1 3 (R66) 


D28 


E6000H 


NASI -10000-1 3 (R31) 


C61 


E60001 


L88316 


016 


E6000I 


L88316 


017 


E6000K 


NASl-1O0OO-13(R52) 


D23 


E6000K 


NASI -10000 


D36 


E60000 


L75052 


002 


E60000 


L8it253 


003 


E60000 


L8499^-6 


009 


E60000 


L8it99'+-7 


010 


E60000 


L8i+99^-8-9 


Oil 


E60000 


L88316 


016 


E60000 


L88316 


017 


E60000 


NASI -9776 


002 


E60000 


NASI -10000-1 3 (R^) 


D16 


E60000 


NASI -10000-1 3 (R59) 


D25 


E60000 


NASI -10000-1 3 (R85) 


D32 


E60000 


NAS1-10000-39(53D) 


D66 


E6000R(6000Z) 


L55255 


Oil 


E6000R(6000Z) 


L55255 


012 


E6000P 


NASI -10000-1 3 (R61) 


FIO 


E6000R 


NASl-100OO-13(R^9) 


D13 


E6000R 


NASl-1O0OO-13(R3'+) 


D\k 


E6000R 


NASI -10000-1 3 (R^O) 


D15 


E6000R 


NASI -10000-1 3 (R^8) 


D19 


E6000R 


NASI -10000-1 3 (R63) 


026 


E6000R 


NASl-10000-27(S2i+) 


D33 


E6000R(R1257) 


NAS1-11867 


001 


E6000R 


NASI -1 2500 (R33) 


H31 


E6000R 


NASI -1 2500 (Rii3) 


H32 


E6000R 


NASI -1 2500 (R11) 


H33 


E6000R 


NASI -1 2500 (R1 6) 


H35 


E6000T(R1257) 


NASI -11859 


002 


E6000U 






E6000Z(RAS159) 


NAS1-6935(T18) 




E6000Z(RAS173) 


NASI -6935-1 (T18) 




E6000R 


NAS1-I0if84-Z 


005 


E6000R 


NASl-10it83-Z 


004 


E6183F 


NASI -10000 


F37 


E6184F 


NASI -10000 


G03 


E6184N 


NASI -10000 


G29 


E6187F 


NASI -10000 


837 


E6189Y 


NAS1-12500-16(S01) 


178 


E6190F 


NAS1-1O0OO 


88it 


E6191F 


NASI -10000 


885 


E6191J 


NASI -1 0000 (R62) 


C16 



OBLIGATION 



HEP Mod. Antares MB Nozzle $ 

Phase Vl Vehicle Processing 

SAMTEC Range Support 

SAMTEC Range Support 

Nozzle Data Book 

Phase VI Certification Training 

WTR Operations & Maintenance SAMSO 

Mods to Magazine at NAD 

Motor Storage at NAD 

Storage Rocket Motor - Nevada 

U.S. NAD - Storage & Handling 

Range Costs 

Range Costs 

Evaluat Strain & Force lnstr.,WI 

Hydrotest Antares MB Case 

Fourth-Stage Ignition System 

Inspection of X-259 Motor 

G.S.E. Changes 

Phase VI Motor Procurement 

Phase VI Motor Procurement 

Transfer of Personnel 

Temperature Conditioning Castor#27 

Static Test X-259 HIB211 

Data Computer Program 

Mod. Cool Air WTR/WI 

Aging Thixon AB894 

5 Instrumentation Kits for X-259 

NOT Technical Study 

Altitude Test for 60-lb. Motor 

Scout Simulators, 1/20 Scale 

Verticality Sensor Mounting Bracke 

Shelf Life 1st and 2nd Initiators 

Technical Support by TCC 

Suppl ies 

Algol Nozzles Rebuilt 

Algol Nozzles Rebuilt Adjustment 

Technical Support by UTC 

Technical Support by Hl/B 

UK-4 Rel iabil i ty 

MTS-A Rel iabil i ty 

MTS-A Launch Site Services 

UK-5 Rel iabi 1 i ty 

ANS-A Mod. to Accept Algol III 

SM-C2 Rel iabi 1 ity 

Hawkey e Reliability 

Hawkeye Castor II Sh.Lf.Ext. 



.00 
,00 
,00 
.00 



3,368.00 
8,162.00 
10,000.00 
14,922.00 
27,685.00 
15,948.00 

I ,500.00 
24,000.00 

2,500.00 

2,500.00 

15,200.00 

10,000.00 

14,922.00 

150.00 

46,897.00 

5,666.00 

3,474.00 

44,359.00 

25,000.00 

5.833. 
30,096. 

5,362, 

3,468, 
72,709.00 
10,864.00 
12,833.00 
59,910.00 
119,325.00 
13,295.00 

1 ,035.00 
t 3,286.00 

1,784.00 
44,665.00 
32,556.22 

348,500.00 
-31 ,000.00 

27,787.57 

43,154.00 

176,842.00 

205,030.00 

10,630.11 

205,052.00 

II ,855.00 
142,732.00 

88,532.00 
23,643.00 



341 



TABLE LXXXV Concluded - FY 1973 NASA PRODUCTION (490) OBLIGATIONS 
PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6l91(i 
E6I9IQ 
E6I9IR 
E6I9IR 
E6I9IR 
E6I9IY 
E6I9IY 
E6I9IZ 



NASI -12500 
NASI -12500 
NASI -10000 
NASI -12500 
NASI -12500 

NASI -71 99 
NASI -10500 
NAS1-11400 



ITEM DESCRIPTION 

(RIO) 218 Hawkeye 4th Stg .w/H.P.X259 $ 
(R24) 229 Hawkeye BE3A9 Motor Flight Prep. 
(R71) CI 9 Hawkeye Test w/S trap-on Motors 
(R5) 214 Hawkeye Range Safety NPE Data 
(R38) 240 Hawkeye BE3A9 Motor Nozzle Plugs 

561 Hawkeye Vehicle Procurement 
-04 008 Attitude Correction System 
030 Hawkeye Motor Procurement 
Shipping 
STS DIRECT - MSEC 

DCASO 
Suballotment - Wallops 
WTR 
Goddard 



IMS 



TOTAL 



OBLIGATION 

105,827.00 

5,388.00 

7,386.00 

1,235.00 

2,743.00 

420,358.00 

47,107.00 

77,600.00 

56,227.53 

4,000.00 

125,000.00 

(204,625.33) 

(122,712.32) 

( 9,600.00) 

514,130.88 



$ 3.342,236-31 



TABLE LXXXV I - FY 1974 NASA PRODUCTION (490) OBLIGATIONS 

PHASE V 
PHASE VI 
PHASE VI I 
SUBAUTHORIZATION 
TOTAL 



ITEM DESCRIPTION 



PHASE VI 






JOB ORDER NO. 


ORDER NO. 


ITEM 


E6OOOA 


NASI -10000 


D68 


E6OOOE 


NASI -10000-1 3 (R69) 


D70 


E6000H(RAS159) 


NASI -6935 (T1 3) 




E6000H(RAS159) 


NAS1-6935-7(T13) 




E6000H 


NAS1-10000-37(C28) 


676 


E6000I 


L883I6-3 


019 


E6OOOI 


L883I6-3 


020 


E6000I 


L883I6-4 


018 


E6OOOI 


NASI -10000-1 3 (R41) 


D34 


E6OOOI 


NAS1-12500(J-1) 





$ 13,337.69 

3,762,536.07 

3,790,712.69 

209.778.78 

$7,776,365.23 

OBLIGATION 



CAS-B Program Management $ 

Support to LRC Anomaly Investg. 

Design Change S-Band T/M 

Design Change S-Band T/M 

Assemble 4th Stg. Ign. & T/M 

WTR Ops. £. Ma int. -SAMS 

WTR Ops. & Maint.-SAMSO 

WTR Ops. & Maint.-SAMSO 

Regulator 

San Marco Support 



318,938.00 

23.237.00 

411 ,900.00 

4,961 .00 

4,689.00 

1 ,568.00 

12,432.00 

25.000.00 

34,0i+3.00 

266,845.00 



3^2 



TABLE LXXXVI Continued - FY 197^ NASA PRODUCTION (if90) OBLIGATIONS 



PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6000L 

E60000 

E60000 

E60000 

E60000 

E60000 

E60000 

E60000 

E6000P 

E6000R(RAS183) 

E6000R(RAS183) 

E6000R(RAS173) 

E6000R(RAS159) 

E6000R(RAS173) 

E6000R(RAS173) 

E6000R(RAS159) 

E6000R(RAS195) 

E6000R(RAS190) 

E6000Y 

E6000Z 

E6000Z 

E600GR 

E6000R 

E6180T 

E6180V 

E6181Z 

E6181Z 

E6183W 

E6l8i|Z 

E6184Z 

E6187C 

E61870 

E6187T 

E6187V 

E6187R 

E6189C 

E6189I 

E6189M 

E6189V 

E6189R 

E6I9OC 

E6I9OH 

E6I9OH 

E6I9OU 

E6I90I 



NASI -10000 


D35 


0Lif49 


002 


OlkkSIK 


OOif 


OL77^A 


003 


L18055A 


001 


L84253 


004 


L2866000401 


002 


NAS1-10000-37(C26) 


674 


NASI -10000 


DO3 


NASI -6935-2 (TM) 




NASI -6935-2 (TM) 


Oil 


NASI -6935-2 (T42) 




NASI -6935-3 (T44) 


002 


NASl-6935-^(T^) 


005 


NASI -6935-5 (Tit2) 




NASl-6935-7(Tit4) 




NASI -6935- (T^it) 


003 


NAS1-6935(Tit6) 


002 


NASI -10500-01 -3 


005 


LI 2904 


002 


L55255 


019 


NASl-1048't-5-Z 


007 


NASI- 1048*^-5-2 


008 


NASI -7256 


Ekl 


NASI -7256 


E43 


NAS1-10000-23M 


F29 


NAS1-10000-23M 


F30 


NASl-10000-it8 


G31 


NAS1-10000-23M 


G06 


NAS1-10000-23M 


G35 


NASI -12500 


H41 


NAS1-12500-7(R57) 


h46 


NASI-7256 


E42 


NASI -7256 


EI5 


NASl-10i+84-Z 


030 


NASI -12500 


141 


L7930A 


009 


NASI -10000 


C69 


NASI-7256 


E24 


NAS1-I048it-Z 


031 


NASI -12500 


A24 


NASI -10000-9(03) 


C06 


NASI -10000-39(037) 


C81 


NASI -1 0000- J-1 




NASI -1 2500- J-1 





ITEM DESCRIPTION OBLIGATION 



Phase VI Logistics Adminis. $ 407,971-00 

Electric Hoist - WFC 1,077-08 

Electric Hoise - W7R 1,038.50 

Electric Hoist - WTR 2,077-00 

Mechanical Prototype, Injun I 9,611.00 

Mod. NAD Magazine 17,834.15 

Life Vests 143-94 

Launch Base-A Support Pins 8,525-00 

Phase VI Vought Support at LRC 4,845-00 

Develop 42" Heat Shield 11,336.00 

Heat Shield A-502 Test 32,939-00 

Modified Jet Vane Test 34,234.00 

S-Band Development 58,674.00 

S-Band Development 47,964.00 

Modified Jet Vane Test 74,620.00 

S-Band Development 40,055-00 

S-Band Development (R1257) 107,495-00 

Algol Dollies 129,132.00 
Payload Separation Ignition Timers 20,791-00 

Fire 2 Altair III Motors 25,000.00 

AEDC Test Fire Altair III Motor 570.23 

Technical Support at UTC -12,765-55 

Technical Support at UTC 4,227-36 

CAS-A Production Support 26,161.00 

CAS-A Tooling Maintenance 31,003-00 

AEROS-A Motor, 1st Stg. Initiator 770.00 

AEROS-Z Motor, 2nd Stg. Initiator 770-00 

UK-4 Award Incentive 105,286.00 

MTS-A 1st Stg. Initiator 770.00 

MTS-A 2nd Stg. Initiator 770.00 

UK-5 Pref light Planning 20,455-00 

Inspect X259 HIB-307 on UK-5 6,361.00 

UK-5 Production Support 26,l60.00 

UK-5 Tooling Maintenance 31,003-00 

Technical Support at UTC 1,725-00 

ANS-A Pref light Planning 34,842.00 

ANS-A Range Costs 49,237-97 

ANS-A Spares 65I -00 

ANS-A Tooling Maintenance 31,003-00 

Technical Support at UTC 6,340.00 

San Marco C2 Pref light Planning 8,989-00 

Rework and Test SM-C2 Sep. Syst. 11,604.00 

4th Stage Ignition System 1,301.00 

San Marco Support 189,830.00 

San Marco Support 59,529-00 



,« 



343 



TABLE LXXXVI Concluded - FY 1974 NASA PRODUCTION (490) OBLIGATIONS 
PHASE VI Continued 



JOB ORDER NO. 


ORDER NO. 


ITEM 


DESCRIPTION 


OBLIGATION 


E6191C 


NAS1-12500 


143 


Hawkeye Pref 1 ight Planning $ 


33,510.00 


E6191I 


L5120A 


002 


Lease Com. Lines, New Zealand 


5,396.00 


E6191I 


L6254A 


002 


Hawkeye Air Cooling Dwgs. 


225.00 


E6191Y 


NASI -10500-03-5 


007 


Attitude Correction System 
Stock Issues 
Shipping 
Subal lotment - 

GSFC-SM-C2 Support 

-Castor Motor Hoise Beam 
-IMS (STS Direct) 

WTR 
STS DIRECT - 

DCASO 

SAS-C Launch Costs 
IMS 


60,520.00 
32,743.54 
22,132.32 

(65,000.00) 

(6,404.00) 

(7,994.00) 

(130,380.78) 

250,000.00 

83,000.00 

499,449.53 



TOTAL 



$3,762,536.07 



TABLE LXXXVI I - FY 1975 NASA PRODUCTION (490) OBLIGATIONS 

PHASE IV $ 15,517.00 

PHASE V 340,673.00 

PHASE VI 2,284,180.91 

PHASE VII 9,567,125.35 

SUBAUTHORIZATION (Phase Vll) 91,985.74 



PHASE VI 






JOB ORDER NO. 


ORDER NO. 


ITEM 


E6000 


NAS1-7256-27(C30) 




E6000E 


NASI -10000 


D01 


tbUUUH 


NASl-725b-b 




E60000 


L29062A 


052 


E6OOOR 


NAS1-12500(R16) 




E6000R 


NASI -1 2500 (R53) 


H37 


E6000T 


NASI -7256 




E6000Y 


NASI-IOOOO(RI) 





TOTAL 



ITEM DESCRIPTION 



Algol III Test Components 
Phase VI Systems Engineering 
Vehicle Processing 
T.V. Camera Tower at VAFB 
2nd Stg. Initiator S.L. Test 
Atltitude Test, 60-lb. Motor 
Production Support 
Separat ion/Ign it ion/Timer 



$12,299,482.00 



OBLIGATION 

1 ,607.00 

363,869.92 

74,600.00 

4,410.50 

1,784.00 
14,295.00 
28,720.00 

2,573.00 



3kk 



TABLE LXXXVII Concluded - FY 1975 NASA PRODUCTION (^90) OBLIGATIONS 
PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6183J(RAS190) 

E6183J(RAS196) 

E6183J(RAS196) 

E6183J 

e6183J(RAS190) 

E6183T 

E6184H 

E6187D 

E6187J 

E6187W 

E6187X 

E6189M 

E6189T 

E6189N 

e61 89W 

E6189W 

E6189W 

E6189W 

E6190 

E619OB 

E619OD 

E6I9OT 

E619OW 

E619IM 

E6191T 

E6I9IN 

E6I9IV 

E6I9IW 



ITEM DESCRIPTION 



NASI -6935-3 (T51) 


008 


NASI -6935-^ (T51) 


010 


NASl-6935-^(T51) 


Oil 


NASI -6935-5 (T51) 




NASI -6935 (T51) 


009 


NASI -7256 


Pro 


NASI -10000 


G36 


NAS1-12500(R75) 




NASI-I25OO 


H48 


NASI -12500 




NAS1-12500(r68) 




NASI -12500 


301 


NASI -7256 




NASI -12500 




NAS1-12500 




NAS1-12500(R69) 




NASI -1 2500 (R 73) 




NAS1-7256(R78) 




NASI -72 56-4 (C^t) 




NASI-I25OO 




NASI -12500 




NASI -7256 




NASI -12500 


174 


NASI -12500 


303 


NAS1-7256-27(C21) 




NASI -12500 




NASI -12500 




NASI-I25OO 





$ 



UK-4 E-Section Test Rework 
UK-4 E-Section Test Rework 
UK-4 E-Section Test Rework 
UK-4 E-Section Test Rework Complel 
UK-4 E-Section Test Rework 
Production Support 
MTS-A Vehicle Processing 
Final Fl ight Report 
UK-5 Mission Peculiars 
Incent ive Award 

S/M Guidance Components Delivery 
ANS-A Spares 

ANS-A Production Support 
ANS-A Field Services 
Incent ive Award 
Flight Anomaly Investigation 
Flight Anomaly investigation 
ANS-A Evaluation of Diodes 
San Marco Protective Barriers 
San Marco Mission Integration 
San Marco Final Flight Results 
Production Support 
San Marco C2 Award Incentive 
Hawkeye Spares 
Services for BE3A9 Motor 
Hawkeye Field Services 
Tooling for Hawkeye Mission 
Incentive Award 
Stock Issues 
Shipping 



OBLIGATION 

2,119.00 

1 ,600.00 

1 ,798.00 

:. 1 ,8^+7.00 

8,490.00 

26,169.00 

23,763.00 

38,062.00 

11 ,307.00 

100,000.00 

4,528.00 

60,000.00 

26,160.00 

424,650.00 

100,000.00 

90,744.00 

57,250.00 

5,024.00 

2,398.00 

1 ,974.00 

36,032.00 

26,160.00 

100,000.00 

30,000.00 

2,834.00 

424,650.00 

36,130.00 

100,000.00 

3,566.24 

45,066.25 



TOTAL 



$2,284,180.91 



TABLE LXXXVII I - FY 1976 NASA (490) OBLIGATIONS 

PHASE VI $ 4,101 ,004.55 

PHASE VII & SUBSEQUENT 6,058,752.37 

SUBAUTHORIZATION (Phase Vll) 4l5,243.08 

TOTAL $10,575,000.00 



345 



TABLE LXXXVIII Continued - NASA FY 1976 PRODUCTION (490) OBLIGATIONS 



PHASE VI 



JOB ORDER NO. ORDER NO. 



ITEM DESCRIPTION 



OBLIGATION 



E6000A 

E6000C 

E6000E 

E6000F 

E6000G 

E6000H 

E6000H 

E6000H 

E6000I 

E6000(1 

E6000R 

E6000R 

E6000R(RAS1 

E6000R(RAS1 

E6000V 

E6000V 

E6180B 

E6180B 

E6180C 

E6180M 

E6180Y 

E6181K 

E6181Y 

E6183K 

E6183Y 

E6183Z 

E6183Z 

E6183Z 

E6184K 

E6184M 

E6184T 

E6184Y 

E6184Z 

E6187E 

E6187K 

E6189B 

E6189D 

E6189E 

E6189F 

ctl Ron 

E6189H 
E6189T 
E6189V 
E6190K 
E6190I 



NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
84) NAS 
84) NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 

MAC 

NAS 
NAS 
NAS 
NAS 
NAS 



2500 

0000 

2500 

2500 

2500 

5000 

0000 (R24) 

2500 

2500-J-1 

0000-25(Cl9) 
0000-1 3 (R1 4) 
0000-13 (R25) 
0500-01-2 
0500-01 

9258 
5000 

6020 

6020-37 
0000 
0000-23 
0000-1 5T 
0000-F 
0000-20T 
OOOOF 
0000-1 5T 
0000-23M 
0000-23M 
0000-23M 
OOOOF 
0000-23 
0000 

0000-20T 
0000-2T 
2500 
OOOOF 
2500 
2500 
2500 

2500 
tcnn 

4. ^ vy V 

2500 
2500 
2500 
OOOOF 
2500- J-1 



006 
007 
F78 

El 7 
E18 



Phase VI Management 

CAS-B Pref light Planning 

Phase VI Systems Engineering 

Phase VI Rel iabil ity 

Phase VI Standardization 

Phase VI Processing 

Replacement of GFE Cables 

Phase VI Vehicle Processing 

San Marco Support 

Battery Cel Is 

S imulators 

Test Nitrogen Regulators 

Pay load Timers 

Ship Sets P/L Sep/lgn. T'mers 

Algol III Production Tooling 

Tool ing 

CAS-A Mission Integration 

CAS-A Mission Integration 

CAS-A Pref light Planning 

CAS-A Spares 

CAS-A Production Support 

Cas-A Field Training 

Production Support 

Field Tra ining 

Production Support 

Fourth Stage Initiator 

First Stage Initiator 

Second Stage Initiator 

Field Training 

Spares 

Hawkeye Production Support 

Hawkeye Production Support 

Production Support 

Systems Engineering 

Field Tra ining 

Mission Integration 

Mission Results 

Systems Engineering 

Rel iabi 1 ity 

Vehicle Processing 
Production Support 
Tool ing 

Field Training 
San Marco Support 



342 

22 

284 

187 

46 

5 

19 
266 

1 
30 
30 
30 

3 

170 

43 

2 

25 

50 

28 

2 

6 

2 

28 



2 
47 
2 
6 
1 

2 

6 

20 

239 

134 

220 
1 

37 

2 

59 



,203.00 
,099.00 
,134.00 
,407.00 
,659.46 
,270.00 
355.00 
,679.00 
,845.00 
,200.00 
,305.00 
.731.00 
,580.00 
,027.00 
,000.00 
,503.00 
,535.00 
67.00 
,998.00 
,000.00 
,516.00 
,286.00 
,700.00 
,286.00 
,516.00 
968 . 00 
770.00 
770.00 
,286.00 
,492.00 
,433.00 
,700.00 
,657.00 
416.00 
,286.00 
,991 .00 
,805.00 
,766.00 

,964.00 
otn nn 

,191 .00 
,578.00 
,899.00 
,286.00 
,529.00 



3he 



TABLE LXXXVIII Concluded - NASA FY 1976 PRODUCTION (490) OBLIGATIONS 
PHASE VI Continued 



JOB ORDER NO. 


ORDER NO. 


E6I9IA 


NASI 


-12500 


E6I9IB 


NASI 


-12500 


E6I9ID 


NASI 


-12500 


E6I9IE 


NASI 


-12500 


E6I9IF 


NASI 


-12500 


E6I9IG 


NASI 


-10000 


E6I9IH 


NASI 


-12500 


E6I9IK 


NASI 


-10000F 


E6I9IM 


NASI 


-7102 


E6l9lV(Rl2i+6) 


NASI 


-10500-03-5 


E6I9IW 


NASI 


-15000 


E6I9IO 


NASI 


-7102 


E6I9IR 


NASI 


-7102 


E6I9IR 


NASI 


-7102 


E6I9IR 


NASI 


-7102 


E6I9IR 


NASI 


-7102 


E6I9IR 


NASI 


-7102-1 


E6I9IT 


NASI 


-15000 


E6I9IT 


NASI 


-15000-19 


E6I9IY 


NASI 


-7102 


E6192B 


NASI 


-15100 (R111 


E6192E 


NASI 


-15000 


E6192H 


NASI 


-15000 


E6192H 


NASI 


-15100(r66) 


E6192H 


NASI 


-15100 (R83) 


E6192H 


NASI 


-15100 (RII9 


E6192M 


NASI 


-15100 


Eb192M 


NASI 


-15100 


E6192M 


NASI 


-15100 


E6192Y 


NASI 


-15000 



ITEM DESCRIPTION 



006 



$ 



Hawkeye Management 

Hawkeye Mission Integration 

Hawkeye Results 

Hawkeye Systems Engineering 

Hawkeye Reliability 

Hawkeye Standardization 

Hawkeye Vehicle Processing 

Field Tra in ing 

(16) Spare Detonators 

Hawkeye Tooling Maintenance 

Hawkeye Award Incentive 

Balance Fixture 

BE3A9 Mockup 

BE3A9 inert Motor 

2 BE3A9 Test Motors 

Documentat ion 

Improvements & Testing BE-3 Mtr. 

Production Support 

Production Support 

BE3A9 #3 5th-Stg. Motor 

Preliminary Trajectory 

Systems Engineering 

Vehicle Processing 

4th-Stage Instrumentation 

Rework Roll -Yaw Unit 

H2O2 Tanks, Bladder Processing 

First Stage Initiator 

Second Stage Initiator 

Fourth Stage Initiator 

Heat Shield 

Stock Issues 

Sh ipping 



OBLIGATION 

234,9'+3.00 

16,287.00 

49,498.00 

195,077.00 

128,666.00 

29,304.00 

209,933.00 

2,286.00 

3,200.00 

3,575.00 

100,000.00 

5,000.00 

11 ,300.00 

37,000.00 

74,000.00 

18,500.00 

101 ,875.00 

34,858.00 
18,274.00 
72,000.00 
56,438.00 
10,722.00 
74,312.00 
22,005.00 

19,911 .00 

19,740.00 
770.00 
770.00 
968.00 

70,490.50 
481 .84 
901.75 



TOTAL 



$4,101 ,004.55 



TABLE LXXXIX - NASA FY 197T PRODUCTION (490) OBLIGATIONS 

PHASE VI 
PHASE VI I 



$ 73,440.00 
3,326,560.00 



TOTAL 



$3,400,000.00 



347 



TABLE LXXXIX Concluded - NASA FY 197T PRODUCTION (490) OBLIGATIONS 



PHASE Vi 




JOB ORDER NO. 


ORDER NO. 


E6180Z 


NASI -10000 


E6180Z 


NASI -10000 


E6180Z 


NASI -10000 


E6I9OZ 


NASI -10000 


E6I9OZ 


NASI -10000 


E6I9IM 


NASI -12500 


E6I9IR 


NAS1-10483-Z 


E6189Z 


NASI -12500 


E6189Z 


NASI -12500 


E6191Z 


NASI -12500 


E6191Z 


NASI -12500 



TABLE XC 





ITEM 


DESCRIPTION 


Initiator 






OB LI GAT 
$ 770 


ION 






First Stage 


.00 






Second Stage 


Initiator 






770 


.00 






Fourth Stage 


Initiator 






968 


.00 






First Stage 


Initiator 






770 


.00 






Second Stage 


Initiator 






770 


.00 






Spares 








62,432 


.00 




014 


Hawkeye Tech 


nical Support- 


■Hl/B 


3,880 


.00 






First Stage 


Initiator 






770 


.00 






Second Stage 


Initiator 






770 


.00 






First Stage 


Initiator 






770 


.00 






Second Stage 


Initiator 






770 


.00 






TOTAL 








$ 73,440 


.00 


NASA 


FY 1977 


PRODUCTION (490) OBLIGATIONS 










PHASE IV 








$ 5,065 


.38 






PHASE V 








222,533 


44 






PHASE VI 








850,377.92 






PHASE VII & 


SUBSEQUENT 






6,351,541 


26 






SUBAUTHORIZATION (Phase 


Vli) 


270,482 


00 



PHASE VI 




JOB ORDER NO. 


ORDER NO. 


E6OOOF 


NASI -6020-10 


E6OOOF 


NASI -6020-31 


E6OOOG 


NASI -12500 


E6OOOM 


NASI -6020-5 


E6OOOM 


NASI -6020-20 


E6OOOO 


L84253 


E6000R 


NASI -1 0482 -Z 


E6OOOZ 


L55255 


E6180W 


NASI -10000-48 


E6I8OY 


NASI -7199-14 


E6181Y 


NASI -7199-14 


E6183V 


NASI -7256 





TOTAL 






$7,700,000 


.00 


ITEM 


DESCRIPTION 








OBLIGATION 




Off-Site Representat 


ive 




$ 


28,800 


.00 




Off-Site Representat 


ive 






7,420 


.00 


H29 


AEROS-A Standard izat 

Spares 

Spares 


'on 






32,805 

83,842 

3,679 


.54 
.00 
.00 


005 


San Marco C2 GSE 








1.133 


.85 


007 


Test Firina 1 Altair 


1 1 lA 


. AEDC 


4^.180 


.64 


026 


Test Firing 1 Altair 


IIA, 


AEDC 




478.87 




Award Incentive 








105,286 


.00 




Scout Hardware 








52,281 


.00 




Scout Hardware 








52,281 


.00 




Tool ing 








31 ,003 


.00 



348 



TA'lsLE XC Concluded - NASA FY 1977 PRODUCTION (490) OBLIGATIONS 



PHASE VI Cont 


inued 










JOB ORDER NO. 


ORDER NO. 


ITEM 


DESCRIPTION 




OBLIGATION 


E6183W 


NASI -10000 




Award Incentive 




$ 105,286.00 


E6184T 


NASI -7256 




Production Support 




26,161 .00 


E6184V 


NASI -7256 




Tool ing 




31 ,003.00 


E6184W 


NASI -10000-48 




Award Incentive 




105,286.00 


E6184Y 


NASI -71 99 




Scout Hardware 




52,281 .00 


E6l8iiZ 


NASl-7256-27(S21) 




Motors 




2,427.00 


E6184Z 


NASI -10000 




MTS-A Inisiators 




968.00 


E6187Z 


NASI -10000 


850 


UK-5 Initiators 




968.00 


E6189H 


NAS1-10000-37(C25) 




Safe Arm Unit Mod . 




10,779.00 


E6189Z 


NASI -12500 


848 


ANS-A 4th Stage In" 


t iators 


968.00 


E6190H 


NAS1-10000-37(C25) 




Safe Arm Unit Mod . 




10,779.00 


E6190Z 


NASI -10000- 


C38 


San Marco C2 Initiators 


968.00 


E6191Z 


NASI -12500 


846 


Hawkeye 4th Stage 


ni tiators 


968.00 


E6192M 


NASI -15000 




Spares 




50,000.00 


E6000I 


L29075A 


005 


Range Costs 




7,345.02 



TOTAL 



$ 850,377.92 



TABLE XCI - NASA FY 1978 PRODUCTION (490) OBLIGATIONS 

PHASE IV 
PHASE V 
PHASE VI 

PHASE VII & SUBSEQUENT 
SUBAUTHORIZATION (Phase VII) 
TOTAL 



$ 2,600.00 

2,767.00 

990.884.50 

15,184,748.50 

118,363.00 

$16,299,363.00 



PHASE VI 



JOB ORDER NO. ORDER NO. 



(R AS 189) 

(RASI92) 

|(RAS190) 

'(RASI73) 

|(RAS159) 



E6000E( 

E6OOOGI 

E6000H( 

E6OOOO1 

E6OOOO I 

E6000Q 

E6000Q 

E6000R(RAS173) 



NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 
NASI 



-6935 (t49) 
-6935 (t47) 
•6935 (t48) 
■6935 (T35) 
-6935-1 (T35) 
■5592 
-4664 
-6935 (T38) 



ITEM DESCRIPTION 



018 
062 



Separation System Planning Man. 
Scout Std. Procedures/AMM. Depot 
E-Section Marman Clamp & Ring 
SBASI G.S.E. 
SBASI G.S.E. 

Contract Final Costs Adjustment 
Contract Final Costs 
FW4S Shelf Life Extension 



OBLIGATION 

f 10,490.00 

13,600.00 

11 ,430.00 

29,500.00 

7.257.00 

52.50 

9,224.00 

84,000.00 



3h3 



TABLE XCI Concluded - NASA FY 1978 PRODUCTION (U90) OBLIGATIONS 
PHASE VI Continued 



JOB ORDER NO. ORDER NO. 



E6000R(RAS159) 
E6000R(RAS159) 
E6000R(RAS159) 
E6000R(RAS159) 
E6000R(RAS159) 
e6183H'VRAS173) 
e6191R(RAS159) 
E6191Y(RAS159) 



NASI -6935 
NASI -6935 
NASI -6935 
NASI -6935 
NASI -6935 
NASI -6935 
NASI -6935 
NASI -6935 



(T40) 
-4(T40) 

(TVf) 
(T50) 

(T37) 
(T37) 



ITEM DESCRIPTION 



OBLIGATION 



Algol MB Comp. Nozzle Mat. Desn. $617,000.00 



Reduce Proof Pressure Reqmts. 

X258 and BE3A9 Shelf Life Ext. 

S-Band Development 

4th Stage Spin Bearing Tests 

E-Section #31 Mods 

Hawkeye G-Section Test 

Hawkeye G-Section 

Shipping 

TOTAL 



-350.00 

75,239.00 

98,687.00 

6,260.00 

15,400.00 

5,780.00 

5,780.00 

1.535.00 

$990,884.50 



PHASE VI 



E6OOO I 
E6OOOU 



TABLE XCI I - NASA FY 1979 PRODUCTION (490) OBLIGATIONS 

PHASE VI 

PHASE VII & SUBSEQUENT 
SUBAUTHORIZATION 

TOTAL 



JOB ORDER NO. ORDER NO. 



L29075A 
NASI -16520 



ITEM DESCRIPTION 



009 Range Costs, SAMTEC 

002 Phase VI Data Compilation 

TOTAL 



$ 85,604.40 

10,309.395.60 

165,000.00 

$10,560,000.00 

OBLIGATION 

$ 2,114.40 
83,490.00 

$ 85,604.40 



Tables XCI I I through CV I present the Air Force and Navy Program Obligations, 

The summary of obligations noted is as follows: 

Phases prior to VI $28,612,347.69 

Phase VI 10,670,081 .12 

Phases Subsequent through 1977 25,317,420.42 



350 



TABLE XCIIl(a)- SCOUT-AIR FORCE FY 1962 OBLIGATIONS 
(62-6) (63-29) (63-32) 



PHASE II $1.967.W8.37 

PHASE III 1.615,803. its 

PHASE IV _5j02li52^tii5 

TOTAL $8,604,826.00 



TABLE XCIII(b)- SCOUT-AIR FORCE FY 1963 OBLIGATIONS 
(62-6) (63-29) (63-32) 



PHASE II $2,359,030.24 

PHASE III 901,787-09 

PHASE IV 2,574.232.67 

PHASE V 2.046.00 

TOTAL $5,837,096.00 



TABLE XCIIi(c)- SCOUT-AIR FORCE FY 1964 OBLIGATIONS 
(63-29X62-6) 



PHASE II $ 108,310.00 

PHASE III 458,118.20 

PHASE IV 157.852.80 

TOTAL $ 724,281 .00 



TABLE XCIV - SCOUT-AIR FORCE FY 1965 OBLIGATIONS 
(62-6) (63-29) (65-42) 

PHASE II $ 200,000.00 

PHASE II I 447.916.73 

PHASE IV 2,066,779.77 

PHASE V 5 ,361.50 

TOTAL 2,720,058.00 

TABLE XCV - SCOUT-AIR FORCE FY 1966 OBLIGATIONS 
(63-29) (65-42) 

PHASE II $ 200,000.00 

PHASE IV I.727.8O7.58 

TOTAL $1 .927,807.58 
(^^Does not Include 609A or Direct Navy Program (492) 



351 



TABLE XCVI - SCOUT-AIR FORCE FY 196? OBLIGATIONS 
(DOD 62-6 & 66-95) 



PHASE VI 



J.O. NO, 



ORDER NO, 



E6001E NASI -10000 

E6001E NASI -1 0000 (R 7) 

E6001F NASI -1 0000 (R1 6) 

E6001 I L-88316 

E6001I L-88316-2 

E6001J NASI -1 0000 (R3 7) 

E6001J NASI -1 0000 (R36) 
E60010(R9205) L- 75052 

E6001U L-84997 

E6001U NASI -4664 

E6001U NASI -4664 

E6001U NASI -4664 

E6001U NASI -4664 

E6001U NASI -4664 

E6178A NASI -7256 

E6178C NASI -7256 

E6I78D NASI -12500 

E6I78E NASI -7256 

E6I78E NASI -10000 

E6178F NASI -7256 

E6I78G NASI -7256 

E61^H NASI -7256 

E6I78H NASI -7256-3 

E6I78N NASI -10000 

E6178N NAS1-10000-11 

E6I78R NASI -1 2500-1 8-R 18 

E6I78R NASI -7256-28 

E6I78W NASI -10000-29 

E6I78Y NASI -5610 

E6I78Y NASI -71 99 

E6I78Z NASI -561 0-9 

E6I78Z NASI -561 0-4 

E6178Z NAS1-10000-2T 



PHASE IV 
PHASE V 
PHASE VI 
PHASE VII 
TOTAL 

ITEM DESCRIPTION 



976 
D40 
d41 
021 
022 
D43 
D44 

008 

042 

043 

044 

046 

055 

504 

498 

146 

525 

FI5 

528 

533 

543 

722 

B21 

B27 

258 

553 

E59 

142 

613 

E53 

E54 

F11 



$ 5,537,159.13 

2,182,283.69 

3,570,854.92 

450.58 0.47 

$11,740,878.21 



Systems Engineering $ 

Altair I I I Test Fixture 

S/L Initiator 

Navy S-179 Costs 

Navy S-179 Costs 

SOP Volume VI I 

Rol 1-Yaw Simulators 

WTK FY 73 Ops. & Maint.-SAMSO 

LRC Support 

LRC Support 

LRC Support 

LRC Support 

LRC Support 

LRC Support 

Administration 

Pref light Planning 

Data Analysis 

Systems Engineering 

Systems Engineering 

Rel iabil ity 

Standardization 

Vehicle Processing, NA-16 

Install Cork, Base A Fins, NA-16 

Field Services 

Field Services 

Spin Anomaly, NA-16 

Castor Shelf Life Extension 

Award Incentive, NA-16 

Heat Shield A-O5O 

Vehicle Procurement, NA-16 

Algol Squib Ret. Assy. 

Algol IIB Initiator 

Third-Stage Initiator 



OBLIGATION 

5,245.00 
1 ,046.00 
1,863.00 
25,000.00 
28,922.00 
13,069.00 
5,665.00 
10,000.00 
58,960.00 
34,695.00 
7,809.00 
1 ,000.00 
6,500.00 
456,206.23 
205,260.00 
3,059.00 
32,591.00 
140,039.00 
1,132.00 
119,517.00 
58,863.00 
148,281 .00 
1 ,003.00 
386,217.00 
7,011.00 
5,814.00 
405.00 
105,286.00 
16,500.00 
420,358.00 
350.00 
538.00 
1.656.40 



352 



TABLE XCVI Completed - SCOUT-AIR FORCE FY 1967 OBLIGATIONS 

(DOD 62-6 & 66-95) 



PHASE VI Continued 



J.O. NO. 


ORDER NO. 


E6182A 


NAS1- 


■10000 


E6182C 


NAS1- 


■10000 


E6182D 


NASl- 


-10000 


E6182E 


NAS1- 


■10000 


E6182H 


NAS1- 


■10000 


E6182J 


NASI- 


■10000 


E6182M 


NASI- 


-10000 


E6182N 


NAS1- 


-10000 


E6182N 


NAS1- 


■10000-1 


E6182V 


NASI- 


-10000 


E6182W 


NASI- 


-10000 


E6182Z 


NASI- 


-7199-1 


E6182Z 


NASI 


-10000 


E6182Z 


NASI 


-10000 


E6182Z 


NASI 


-10000 


E6182Z 


NASI 


-10000 



ITEM DESCRIPTION 



758 
788 
B33 
D56 
G12 

945 
B24 

E61 

G15 
G86 
E62 
E63 
G13 
997 



OBLIGATION 

Administration $ 318,938.00 

Pref light Planning 32,292.00 

Data Analysis 'tl ,959-00 

Systems Engineering 2,255'00 

Processing 150,371.00 
Cooling Air Sep. H/S Aif06 & Sup. 36,325-00 

Spares 40,000.00 

Field Services 386,217-00 

Field Services 3,119-79 

Tooling Maintenance 65,262.00 

Award Incentive 105,286.00 

Third-Stage Motor 74,188.00 

First-Stage Motor 770.00 

Second-Stage Motor 770.00 

Third-Stage Initiator 1,656.40 

FW-4S Initiators, NA-15 968.00 

Shipping 617-10 



TOTAL 



$3,570,854.92 



TABLE XCVI I - SCOUT-AIR FORCE FY 1968 OBLIGATIONS 
(DOD 66-95 Sr 68-71) 

PHASE IV 

PHASE V 

PHASE VI 

PHASE VI I 

TOTAL 



$ 59,313-00 

271,311-49 

2,094,883.04 

5,011,833-91 

$7,437,341-44 



PHASE VI 




E60010 


L-29062A 


E60010 


L-29062A 


E6001R 


NASI -1 0481 -Z 


E6002I 


L-7930A 


E6002 1 


L- 5098a 


E6002R 


L-55255Z 


E6002R 


L-55255Z 


E6002Z 


L-55240 


E61 78M 


NAS1-10000 



053 T.V. Camera Tower at VAFB $ 4,410.50 

988 T.V. Camera Tower at VAFB 4,410.50 

005 Technical Support by Hercules 157,391-00 
WTR Range Support 2,694.22 

009 50% WTR FY 75 Ma int. & Ops. 37,500.00 

007 AEDC Test Firing X-259 13,223-74 

008 AEDC Test Firing X-259 13,233-74 

006 Antares Casting Powder 58,015-52 
Spares 40,000.00 



353 



TABLE XCVII Concluded - SCOUT-AIR FORCE FY I968 OBLIGATIONS 

(DOD 66-95 & 68-71) 



J.O. NO. ORDER NO. 
PHASE VI Cont i nued 



E6I78T 
E61 78T 
E61 78V 
E61 78Y 
E61 78 Y 
e61 78 Y 
e61 78z 
e61 78z 
e61 78z 
E61 78Z 
E61 78Z 
e61 78z 
E61 78z 
e61 78r 
E61 78R 
E61 79J 
E61 79C 
E61 79E 
E6I791 
e61 79H 
E61 79M 
E61 79R 
E61 79V 
E6182B 
E6182B 
E6182Y 
E6182Y 
E6182Z 
E6182Z 
E6182Z 
E6192C 
E6192E 
E6192E 

E6192H 
E6192H 
E6192M 
E6192R 
E6192W 
E6192Y 
E6192Z 
E61°2Z 
E6192Z 
E6192Z 
E6192Z 
E6192Z 
E6192Z 



NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

L- 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 

NAS 
NAS 
NAS 
NAS 
NAS 
NAS 
NAS 

MAC 

NAS 
NAS 
NAS 
NAS 
NAS 



883 



-6020- 7- E 

-6020-1 5-E 

-7256-V 

-7199-1^ 

-7199-14 

-7199-23 

-5883-3 

-7199 

-7199-1 

-7199-4 

-10000-M 

-10000-M 

-10000-M 

-10481-Z 

-10482-Z 

-I25OO-RI43 

-10000 

-10000 

16 
-7256-3 
-7256 
-7256-28 
-7256 
-6020 

-6020-37 

-7199-14 

-7199-14 

-7199 

-7199-16 

-7199-4 

-12500 

-12500 

-15000 

-12500 

-12500-R91 

-12500 

-12500-R4 

-15000 

-7199 

-I25OO-RI73 
_i 9cnn_DiQi 

-14200 

-I5OOO-M 

-15100 

-I5IOO-M 

-15100-M 



1 itn 


UtbLKIPTION 




OB L 1 GAT 1 ON 




X-258 Off-Site Rep. 


$ 


61 ,477.00 




X-258 Off-site Rep. 




8,667.00 


E37 


Tooling Maintenance 




31,003.00 


G90 


S-Band 




44,689.00 




Roll -Yaw 




6,680.00 


G75 


SBASI Harness 




108.00 




Fourth-Stage Motor 




34,501 .00 


G91 


Second-Stage Motor 




96,215.00 


G99 


Third-Stage Motor 




74,188.00 


G92 


First-Stage Motor 




122,720.00 


F12 


First-Stage Initiator 




770.00 


FI3 


Second-Stage Initiator 




770.00 


F14 


Fourth-Stage Initiator 




968.00 




Technical Support to Fourth 


Stag 


e 3,006.00 




Second-Stage Technical Support 


4,811 .00 




gfe s-179 




8,071 .00 


FI9 


Pref light Planning 




25,673.00 




Systems Engineering 




4,173.00 


486 


Navy S-179 Costs 




55,455.00 


851 


Install Cork, Base A Fins, S 


-179 


1 ,004.00 


e40 


Spares 




8,692,00 




Castor Shelf Life Extension 




405.00 




Tooling Maintenance 




31,003.00 


520 


Mission Integration 




2,926.00 


EI9 


Mission Integration 




77.00 




Eoll-Yaw 




6,680.00 


578 


S-Band 




44,689.00 


609 


Second-Stage Motor 




96,215.00 


610 


Fourth-Stage Motor 




75,437.00 


G98 


First-Stage Motor 




122,720.00 


H27 


Pref 1 ight Planning 




11,203.00 


H25 


Systems Engineering 




7,012.42 


H66 


Systems Engineering 




9,831 .00 




Recertif icotion 




166,616.00 


H26 


Retest Guidance System 




12,214.00 


302 


Spares 




13,871 .00 




Vehicle Instrumentation 




4,474.00 


H63 


Award Incentive 




100,000.00 


583 


Vehicle Hardware 




210,358.00 


828 


Antares Retest 




18,986.57 




Fourth-Stage Motor Change 




66.085.00 


009 


Third-Stage Motor 




51 ^615. 00 


H62 


Third-Stage Initiator 




968.00 


012 


Fourth-Stage Initiator 




968.00 


017 


First-Stage Initiator 




770.00 


018 


Second-Stage Initiator 




770.00 




Shipping 




3,754.32 


_^ 


Travel 




14,409.51 




TOTAL 


$2 


,094,883.04 



354 



TABLE XCVIII 



TABLE XCIX 



SCOUT-AIR FORCE FY 1969 OBLIGATIONS 
(DOD 63-29) (62-6) 



PHASE IV 

DIRECT FIELD SERVICES 

TOTAL 



SCOUT-AIR FORCE FY 1970 OBLIGATIONS 
(DOD 66-95) 



TABLE C 



PHASE VI 




J.O. NO. 


ORDER NO. 


E6001 1 
E6OOIO 


L-883I6 

NASI -1 0000 (R33) 



TOTAL 

SCOUT-AIR FORCE FY 1971 OBLIGATIONS 
(DOD 66-95) 

PHASE V 

PHASE VI 

PHASE VI I 

TOTAL 



ITEM DESCRIPTION 



023 
386 



50% WTR FY 74 Ops. & Ma int. 
Heat Shield Ducting for RTG 



$326,183.30 

158.350.00 

$484,533.30 



PHASE VI 


ORDER NO. 

NASI -4664 
NASI -10000 
NASI -6935 (T5) 
L-29075A 


ITEM 

054 
E93 

F61 


PHASE VI 

PHASE VI 1 
TOTAL 

DESCRIPTION 

LTV Support 
Mission Integration 
Roll-Yaw Unit 
WTR Range Services 


$ 970,882.77 
50.048.23 

$1 ,020,931 .00 


J.O. NO. 


OBLIGATION 


E6001 E 
E6182B 
E6182Y 
E6OOIO 


$ 932,207.35 

7,588.00 

6,680.00 

24,407.42 



$ 970,882.77 



$ 263.678-50 
617,677.16 
731.999.62 

$1,613,355.28 

OBLIGATION 

$ 10,000.00 
21,934.00 



355 



TABLE C Concluded 



SCOUT-AIR FORCE FY 1971 OBLIGATIONS 
(DOD 66-95) 



J.O. NO. 


ORDER NO. 


ITEM 


DESCRIPTION 




OBLIGATION 


E6178H 


NASI -1 0000- (R55) 


E60 


Refurbish Specific 


Sections 1 78 


$ 20,412.00 


E61 78t 


NASI -7256 


E36 


Production Support 




26,161.00 


E61 78y 


NASI -11 000 


087 


Dummy Rol 1-Yaw 




200.00 


E6182H 


NASI -10000-1 3 (R42) 


G21 


RTG Reprocessing Su 


pport 


16,755.00 


E6182N 


NASI -10000-11 


B36 


Launch Ops. Transpo 


rtation 


7,011 .00 


E6182T 


NASI -7256 


E46 


Production Support 




26,161 .00 


E6182V 


NASI -7256 


E47 


Tooling Maintenance 




31 ,003.00 


E6182Y 


NASI -6935-2 (T41) 


038 


Heat Shield 




31,451 .00 


E6182Y 


NASI -71 99 


550 


Vehicle Hardware 




420,358.00 


E6182Y 


NASI -7199-23 


G85 


SBASI Harness 




108.00 


E6182Y 


NASI -6935- (T5) 




Roll-Yaw Unit 




6,680.00 


E6182Y 


NASI -11 000 


068 


Dummy Rol 1-Yaw 

Shipping 

Travel 




200.00 

2,702.47 

-3.459.31 



TOTAL 



$ 617,677.16 



PHASE VI 




J.O. NO. 


ORDER NO. 


E6002 L 


L-793OA 


E6002Z 


L-55240 


E6182R 


NASI -1 0482- Z 


E6182R 


NASI -1 0483- Z 


E6182R 


NAS1-10484-Z 


E6192E 


NASI -15000 



TABLE CI - SCOUT-AIR FORCE FY 1972 OBLIGATIONS 
(DOD 66-95 & 68-71) 

PHASE VI 

PHASE VI I 

TOTAL 



ITEM DESCRIPTION 



010 Range Services 

002 Antares Casting Powder 

Technical Support, 2nd Stg. 

Technical Support, 3rd Stg. 

Technical Support, 1st Stg. 

Systems Engineering 

TOTAL 



$ 19,181.50 

582,847.27 

$ 602,028.77 

OBLIGATION 

$ 2,694.22 

646.28 
4,811.00 
3,744.00 
3,772.00 
3,514.00 

$ 19,181.50 



- ^ 



356 



PHASE VI 



TABLE CM - SCOUT-AIR FORCE FY 1973 OBLIGATIONS 
(DOD 66-95) 

PHASE VI 
PHASE VII 



$ 14,7^6.08 
49,40^1.92 



TOTAL 



$ 64,151.00 



Shipping 
Travel 

TOTAL 



$ 27.08 

14.719.00 

$ 14,746.08 



TABLE CM I - 



SCOUT-AIR FORCE FY 1974 OBLIGATIONS 
(DOD 68-71 ) 



PHASE VI 

J.O. NO. 

E6002U 

E6002H 

E6002 i 

E6002V 

E6179M 

E6182N 

E6192B 

E6192B 

E6192C 

E6192E 

E6192H 

E6192T 

E6192T 

E6192T 

E6192Y 

E6192Y 

E6192Y 

E6192R 

E6192Y 

E6192Z 

E6192Z 

E6192H 

E6192H 

E6192H 







PHASE VI 


^ 779.046-70 






PHASE VII 


10.871.206.03 






TOTAL 


$11,650,252.73 


ORDER NO. 


ITEM 


DESCRIPTION 


OBLIGATION 


L-12905A 


002 


Progress Report 


$ 69.60 


NASI -15000 




Vehicle Processing 


5,242.00 


L-5098A 


010 


Range Costs 


36,077.00 


NASI -15000 




Tool ing 


43,503.00 


NASI -7256 




Spares 


40,000.00 


NASI -10000-11 




Field Services 


3,891.21 


NASI -12500 


H28 


Mission Integration 


921 .00 


NASI -15000 




Mission Integration 


4,239.00 


NASI -15000 




Pref 1 ight Planning 


24,326.00 


NASI -15000 


H64 


Systems Engineering 


10,722.00 


NAS1-15000 




Vehicle Processing 


73,920.00 


NASI -7256-1 2 




Production Support 


7,650.00 


NASI -15000-9 




Production Support 


35,184.00 


NASI -15000-19 




Production Support 


18,043.00 


NASI -71 99 


593 


Vehicle Hardware 


210,000.00 


NASI -71 99-23 


C14 


Fabricate SBAS 1 Harness 


108.00 


NASI -11 000 


072 


Dummy Rol 1 Yaw 


200.00 


NASI -1 0482- Z 


012 


Technical Support, TCC 


13,882.00 


NASI -15000 




Heat Shield 


70,490.50 


NASI -11 400 




Nozzle/ Igniter Hardware 


991 .00 


NASI -11400 




Third-Stage Case 


64,187.45 


NAS1-15000(R230) 




Rework vehicles S-192 


7,821.00 


NASI -1 5000 (R232) 




Assignment of NOVA- 1 1 to S- 


•192 43,662.00 


NASI -1 5000 (R241) 




Inspect & rework E-Section 


62,023.00 






Shipping 


1,777.48 






Travel 


116.46 






TOTAL 


$ 779,046.70 



357 



PHASE VI 

J.O. NO. 

E6002I 
E60020 
E60020 



TABLE CIV - SCOUT-AIR FORCE FY 1975 OBLIGATIONS 

DOD (68-71) 

PHASE VI 

PHASE VII 

TOTAL 



ORDER NO. 

L-22387A 
L-29062A 
L-29062A 



ITEM DESCRIPTION 



005 SAMTEC Ops. and Maintenance 

17 Facility Mod. & Refurbishment 

18 Facility Mod. & Refurbishment 
Shipping 

TOTAL 



$ 46,363.85 
1,153,636.15 

$1,200,000.00 

OBLIGATION 

$ 37,500.00 
3,691.00 
4,557.00 

615.85 

$ 46,363.85 



TABLE CV - SCOUT-AIR FORCE FY 1976 OBLIGATIONS 

DOD (68-71) 

PHASE VI 

PHASE VI I 

TOTAL 



$2,556,397.91 
4.133,477.36 

$6,689,875.27 



PHASE VI 










J.O. NO. 


ORDER NO. 


ITEM 


DESCRIPTION 


OBLIGATION 


E61 79B 


MAS1-12500(BKH) 


698 


Heat-Shield Design 


$ 2,608.00 


E61 79B 


NASI -1 2500 (BEF) 


699 


Preliminary Trajectory 


3,797.00 


E6179B 


NAS1-12500(BGD) 


700 


Environmental Study 


10,338.00 


E61 79B 


NASI -1 2500 (Rl 65) (JDA) 


712 


Interface Drawing Brochure 


8,410.00 


e61 79D 


NASI -1 2500 (Rl 65) 


711 


Pref light Planning 


20,599.00 


e61 79 D 


NASI -1 2500 (Rl 65) 




Final Report 


42,500.00 


E61 79E 


NASI -12500 


AO3 


Systems Engineering 


48,310.00 


E61 79H 


NASI -1 0000 (RO92) 


F16 


Retest Vehicle Components 


9,258.00 


E61 79H 


NASI -10000 


972 


Vehicle Processing 


148,375.00 


E6179H 


NASI -1 2500 (HGG) 




Personnel From Dallas 


87,794.00 


F61 79H 


NASI -1 2500 (Rl 64) 


709 


P.etest Vehicle Components 


7,411 .00 


E6179H 


NASI -1 2500 (R165)(JDD) 




Fit Check 


16,269.00 


E61 79H 


NASI -1 2500 (R91) 




Retest Guidance Components 


12,214.00 


E61 79H 


NASI -1 2500 (HEK) 


AO5 


Heat-Shield Mods, 


31.675.00 


E61791 


L-29075A 


007 


Range Services 


62.429.00 


E61 79J 


NAS1-12500(R165)(JD) 




Vehicle Reassignment 


12.711.00 


E6179J 


NAS1-12500(R165)(JDE) 




Guidance Reprograming 


5,721.00 



358 





TABLE CV Continuec 


i - SCOl 


JT-AIR FORCE FY 1976 


OBLIGATIONS 




J.O. NO. 


ORDER NO. 


ITEM 


DESCRIPTION 




OBLIGATION 


PHASE VI 


Continued 










E6179M 


NASI -10000 


FI7 


Spares 


$ 


48,021 .00 


E6179N 


NASI -12500 


704 


Field Services 




220,364.00 


E61 790 


NAS1-12500A 


706 


DCASO 




15,080.00 


E6179R 


NAS1-10482-Z 


Oil 


Technical Support, 


2nd Stg. 


6,536.00 


e61 79R 


NAS1-10483-Z 




Technical Support, 


3rd Stg. 


3,880.00 


E61 78R 


NAS1-10484-Z 




Technical Support, 


1st Stg. 


6,180.00 


e61 79 Y 


NASI -11000 


059 


Dummy Rol 1-Yaw 




200.00 


E61 79 Y 


NASI -11 000-10 


B01 


Heat Shield 




40,000.00 


E6179Y 


NAS1-12500(R163)(JB) 


648 


Fourth-Staqe TM 




41 ,947.00 


E61 79Y 


NASI -1 2500 (R49) 




Modify Safe Arm Un 


t 


492.00 


E6179Z 


MAS 1-71 99-4 


g80 


First-Stage Motor 




122,720.00 


E6179Z 


NAS1-7199 


988 


Second-Stage Motor 




96,215.00 


E61 79Z 


NAS1-10000M 


973 


First-Stage Initiator 


770.00 


E61 79Z 


NAS1-10000M 


786 


Second-Stage Initiator 


770.00 


E61 79Z 


NAS1-10000T 




Third-Stage Initiator 


1,656.40 


E61 79Z 


NAS1-10000M 




Fourth-Stage Initiator 


968.00 


E61 79Z 


NASI -11 400 


093 


Third-Stage Motor 




77,600.00 


E61 79Z 


NASI -11400 




Fourth-Stage Motor 




34,501 .00 


E61 79R 


NASI -1 2500 (R1 73) 


788 


Antares Retest 




28,736.00 


e61 79R 


NASI -1 2500 (R1 73) 




3rd Stage Igniter 




9,000.00 


E61 79T 


NASI -7256 


E41 


Production Support 




26,161 .00 


e61 79V 


NASl-10000 


F18 


Tooling Maintenance 


68,502.00 


e61 79W 


NASI-I25OO 


707 


Award Incentive 




100,000.00 


E61 79Y 


NASI -71 99 


G78 


Vehicle Hardware 




420,358.00 


e61 79Y 


NASI-7I 99-14 


G76 


S-Band 




43,638.00 


e61 79Y 


NASI -71 99-14 


G77 


Rol 1-Yaw 




6,680.00 


e61 79Y 


NASI -71 99-23 


G79 


Fabricate SBAS 1 Har 


-ness 


108.00 


E6192I 


L-682OOA 


001 


Range Cost 




152,294.13 


E6192R 


NAS1-10484-Z 




Tech. Supt., 1st & 


4th Stg. 


19,618.18 


E6192T 


NASI -7256 


E31 


Production Support 




18,510.00 


E6192V 


NASI -7256 


E32 


Tool ing 




31,004.00 


E6192Z 


NASI -11400 


FO5 


Fourth-Stage Case 




12,724.00 


E6192Z 


NASI -11400 




2nd Stage Motor 




55.000.00 


E6192Z 


NASI -131 00 




First-Stage Motor 

Shipping 

Travel 




286,147.00 
20,279.94 
14,638.44 



PHASE VI 



TOTAL 

TABLE CVI - SCOUT-AIR FORCE FY 1977 OBLIGATIONS 

PHASE VI 
PHASE VI I 

TOTAL 

Shipping 
TOTAL 



(a) 



$2,556,397.91 



$ 47.19 

2,270,851.85 

$2,270,899.04 

$ 47.19 

$ 47.19 



(a) Includes 197T. 



359 



The decision to appoint the Air Force as contractor for the field crew at 
VAFB was agreed to mutually by the NASA Administrator and the Air Force 
Commanding General. This in effect during fiscal years I967 through I970 
During this time period, D.O.D. paid Vought for all field costs and deducted 
the NASA prorated costs for the Ml PR 66-95 and Ml PR 63-29 from the funding 
due NASA. The amounts, by fiscal years exchanged, for this agreement are as 
fol lows: 

Ml PR 66-95 

FY 1967 $210,372.00 

FY 1968 164,200.00 

FY 1969 12,109.00 

FY 1970 134,250.00 
Ml PR 63-29 

FY 1969 158,350.00 

This deduction from D.O.D. funds due NASA, resulted in NASA prorating D.O.D. 
costs on the Vought management contract for the same amount. 

The total Phase VI (490) obligations summarize as follows in table CVII. 

TABLE CVII - TOTAL PHASE VI (490) OBLIGATIONS 



FY NASA DOD 



OTHERS TOTAL 



966 $ 15,782.00 $ $ $ 15 782 00 

967 136.552.00 3.570.854.92 3. 707 .406 92 
1968 1.046.703.97 2,094,883.04 3 141 587 01 

969 4.105.466.74 4 05 466 74 

970 2,631,067.77 970,882.77 50.000.00 3 65I 95654 

971 6.681.575.41 61 7.677.16 1,500,000.00 8;799.25257 

972 7,569.669.90 T9,T81.50 850,000.00 8.438.851 '40 

973 3.679.173.96 14,746.08 2,652,832.11 6.346 752.15 
Q7C I'tlf'Vo^'^^ 779.046.70 5,723.161.00 10.474.522.55 
q5 f'^l^'^^?'^' ^6.363.85 2,296.078.44 4 626 623.20 
976 "^'^Ol'OO^SS 2,556.397.91 1.035.230.21 7.692.632.67 

197T 73.440.00 73 440 00 

nil IIHIJ-^^ ^7.19 313.781.64 1.164:206:75 

9 8 99 '884.50 120.492.80 1.111:377.30 

1979 85.604.40 85.604.40 

TOTAL $38,223,798.88 $10,670,081.12 $14,541,576.20 $63,435,456.20 



360 



The prorated costs associated with the major Scout contracts are presented 
in this chapter: 

SCOUT CONTRACT FIGURE NO. PAGE NO. 

NASI -5610 105 361 

NASI -6020 106 363 

NASI -6935 107 36^ 

NASI -71 99 108 365 

NASI -7256 109 366 

NASI -9258 110 369 

NASI -10000 111 370 

NAS1-I0if8l 112-3 373 

NAS1-I0if82 112-3 373 

NAS1-I0it83 112-3 373 

NAS1-I0it84 112-3 373 

NASI -10485 112-3 373 

NAS1-10500 112 373 

NASI -11000 112 373 

NASI -11400 114 374 

NASI -12500 115 375 

NAS1-13100 112 373 

NASI 14200 116 376 

NASI -15000 117 376 

NASI-I5100 118 377 

STATISTICAL COSTS 

In order to have complete financial control of a program similar to Scout, it 

is necessary to determine costs for specific requirements. The major unit 
statistics that are presented in detail include the following: 

(1) Reimbursable Programs (Tables CVIII and CIX) 377 

(a) ESRO-IB (Phase V) (Table CX) 378 

(b) ESRO-IV (Table CXI) 379 

(c) AEROS-B (Table CXI I) 380 

(d) United Kingdom (UK-X4) (Table CXI I I) 381 

(e) United Kingdom (UK-5) (Table CXIV) 382 

(f) United Kingdom (UK-6) (Table CXV and CXVl) 384-385 

(g) San Marco (NAS1-10000) (Table CXVl I) 386 
(h) San Marco (NAS1-12500) (Table CXVl I I ) 387 

(i) San Marco (Table CXIX and CXX) 388-392 

(j) DOD Summary of Expenditures (Table CXX I ) 394 

(k) DOD Ml PR 66-95 Cost Summary (Table CXX I I ) 395 

(1) DOD MIPR 66-95 Per-Mission Cost (Table CXI I I) 395 

(m) DOD MIPR 66-95 Annual Cost (Table CXXIV) 396 

(n) DOD MIPR 68-71 Per-Mission Cost (Table CXXV) 397 

(o) DOD MIPR 68-71 Annual Cost (Table CXXVl) 398 
(p) DOD MIPR 68-71 Summary of Expenditures (Table CXXVl 1)399 

NOTE: This list continues on page 399. 



Fi9«r« 10$.- Contract MASl-SfilO - Prorstion of Costs. 
PHASE (V PHASE V 



SCOUT 

VEHICLE 

mmacK wasa 



0RIG5^SAL PAGS B 
OF POOR QUALITY 



Uehtct 


e Hardware 


«nd Heat Shield 


Scout 


less H/S 


Scout 


less H/S 


Scout 


+ H/S A47 


Scout 


+ H/S A58 




+ H/S Al.5 


Scout 


+ H/S AW 


Scoot 


♦ H/S A53 


Scout 


less H/S 


Scout 


Uss H/S 


Scout 


+ H/S A56 


Scout 


t H/S A5^ 


Scout 


+ H/S A57 


Scout 


less H/S 


Scout 


+ H/S A55 


Scout 


less H/S 


Heat •■ 


Shields 




A*3 



163 
lU 
l» 
lU 
It? 
lU 
1(9 



172 
173 
Ilk 
175 
176 



16.500 
16,500 



Hod. 3 - Auto. Destruct Hodule 

Mod. 7 - Fifth-Stag* Mods. 

Mod. 7 - Convert to S. S. Tub«5 

Mod. 9 - CCN is ' Tenp. Mecsuremnts (8 veh.) 



Algol IIB First-Stage Motors: 



61 Test Motor 




62 


160 


63 


172 


6I| 


167 


65 


16% 


66 


175 


67 


169 


68 


176 


69 


163 


70 Test Motor 





AI90I Nozzle Assys. (3) 



Algol Igniter Assys. {k) 



Algol Squib Retainers (2) 



17.380 
17,380 
17,380 

835 
835 
835 



^M.600 
4M.600 
460.100 
460.100 
460,100 
460.100 
460,100 
443,600 
443.600 

460,100 
460.100 

443,600 



18.350 
6.655 



5,642 

2.476 



127,100 
127.100 



127.100 
127,100 
127,100 
127.100 
127,100 
127.100 

127,100 
127.100 
127,100 
127.100 



16,500 
*I6,500 



460.100 
460,100 
460,100 
460,100 
4%3.6O0 
443.600 
460,100 
460,100 
460,100 
443.600 
460.100 
443,600 



16.500 
16,500 
16.500 
16,500 
16,500 
16,500 
16,500 

18.350 
6.655 

3* ,695 
38,750 
6.510 
3.300 



127.100 
127,100 
127.100 
157.100 
127,100 
127,100 
127,100 
127,100 
127,100 
127.100 
127,100 
127,100 
127,100 
127.100 
127.100 
127.100 
127,100 
52,140 



Algol HqzzIb Leak Check Tooftng 

HoiJ. 4 - CCH2 - Algol Initiators 
Hod. 9 - CCHIt - Squib Ret. Assys. 
Hod. 13 - Storaqe of Alools 

Castor 1 1 Second-Staoe Motors 



171 


169 


172 




173 




171. 




175 




176 




177 Test Motor 




178 




179 




180 




181 




182 




183 


166 


18% 


176 



Castor Pyrogen igniter 

Mod. % - CCN5 GFP Castor Case (Test) 



5.923 
3.850 
3.205 



99.680 
99.680 
99.680 
99.680 
99,680 
99.680 
99.680 
99.680 

99,680 
99.680 
99.680 
99.680 

1.693 



538 
350 



538 
350 



8.61lt 
5.600 
3,205 



99,680 
99,680 
99,680 
99,680 
99.680 
99.680 
99.680 
99,680 
99,680 
99,680 
99.680 
99.680 
99.680 
99.680 
99.680 
1.693 

(■S.IOO) 



X-259 Third-Stage Motors 
83 S/N 211 Test Motor 



218 

219 

220 

221 

222 Test Motor 

223 

22l| 

225 

226 



158 
162 
172 
165 
167 
169 



Mod. 7 - CCKIO lte(>air Containers 
Mod. 8 - CC(il2 Third-Stage Init. 
Mod. 8 - CCM 13 £xit Cones (8) Hods. 



FW%S Fourth-Stage Motors 
2223-1 
2223-2 
2223-3 
2223-11 
2223-5 



2223-7 

2223-8 

2223-9 

2223-10 

2223-11 

2223-12 

2223-13 

2223-il( 

2223-15 

2223-16 



167 
168 
17% 
165 
169 



183 
185 



163 



Hod. 7 - CCH3 ET FirtS lk,„l, |„„, i. 
Mod. 8 - CC«I2 Fourth-Stage Initiators 
Hod. 10 - CCNi6 Reinforce Hozrles 
Hod. 10 - CCH17 Test Shipping Containers 
Mod. 15 - CCK12 Leaii Test Hoziles (12) 
Hod. 16 - Refurbish Tooling 



57.060 



57.060 
57.060 
57.060 
57.060 



57.060 
57.060 



7.%80 
6.%29 
3.850 



33.070 
33,070 
33,070 
33,070 
33.070 

35.070 

33,070 
33,070 
33.070 



33.070 
33.070 

23.636 
7.500 

5%, 000 

13,130 
1,257 

2%,8%6 



57,060 



57.060 
57.060 
57.060 
57.060 
57.060 
57.060 
57.060 
57.060 
57.060 
57.060 
57.060 

57!o60 
57.060 
57.060 
S7.06O 

7,%80 
10.000 
3.850 



33.070 
33.070 
33.070 
33.070 
33.070 
33.070 
33,0/0 
33.070 
33.070 
33.070 
33.070 
33.070 
33.070 
33,070 
33,070 
33,070 

23,596 
10,000 
5%, 000 
13,130 
1.257 
2%.8%6 



SUSn^finii 5?37,'i6% S 57.774 s q,75%,l471 $7%a.?ni 5782.396 $233. 2%0 $50, 38fl $ 33.695 $13,3l.3.g33 



SLS - shelf Life Study. 



362 









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riffure 107-- Contrftct IHS1-6935 - Proration of Costs 



PWSE 

I TEH 

Task 1 
H-3 
Task 2 
T«sk 3 
T«sk I* 
Task 5 

H-2 
Task 6 
Task 7 
Task 8 
Task 9 

N-1 
Task 10 

M-3 

M-'t 

N-8 
Task tl 



Hod-6 
Hod- 7 
Hod-9 



n-6 

Task 13 

H-5 

H-7 
Task lit 



Task 15 

H-1 
Task 16 
Task 17 
Task 18 

H-1 
Task 19 
Task 20 
Task 21 
Task 22 
Task 23 
Task 21* 
Task 25 
Task 26 
Task 27 
Task 28 
Task 29 
Task 30 
Task 31 

H-1 

M-2 
Task 32 

H-2 
Task 33 

H-1 
Task iU 

H-2 
Task 35 

H-1 
Task 36 



Task 38 
Task 39 



H-7 
Task U3 
Task U 

H-3 

H-l« 

H-7 

H-9 
Task i«5 
Task lt6 
Task 1*7 
Task 1*8 
Task It9 
Task SO 
Task 51 

H-3 

H-d 

H-5 



M-7 
M-7 



OR!G[^mL PAGE (S 
OF POOR QUALITY 



jot «DCK MO. 

R1226(ltASt>t2) 
R1226(ltASI'(2) 
E1008(RAS1'»9) 
E1008(RAS160) 
E5l6dJ(RAS1't9) 
ltl260(RAS152) 
E5176V 
E6182V 

R1260(RA5152) 
E5000H((tAS1'tO) 
ESOOOR(HASIUO) 
RI226(RAS1ti2) 
(i«JF19'«) 
E516dJ(R*S125) 
R1226(flAS168) 
R1260(ltASlS2) 
E5000R(RAS173) 
E5000R(RAS173) 
e6000H(RAS1'iO) 
E5t69R(RASI'»0) 
E6l80R(RAS1'tO) 
E5l7'ilt(RASII»0) 
E6l83R(RAS1(>0) 
E7198R(RAS1'tO) 
Ett|i»l«Y(RAS1'iO) 
Et»l(i'tR(RASlliO) 
E6I63V(RAS1I>0) 
E6l85ft0lAS11>0) 
E7193R(RAS1'40) 
£5172R(RAS1'tO) 
E517*tV<RAS11tO) 
£6l80V(RAS11*0) 
£5177Y(BAS11*0) 
ESOOOHfRASIUO) 
e6DOOH(HAS159) 
ESOOOH(RASti40) 
E5000H(HAS17<«) 
E5000H(RA$t59) 
E6000ri{RAS159) 
E1008(RASt63) 
E1008(RASI63) 
E500aR(RASI'tO} 
E5000R 

E6000H(RASI59) 
E6000H{RASI T**) 
E6000H(RAS1S9) 
Rt231{RASIS8) 
R3501 (RAS158) 
El»l<*Mt((lASll»0) 
E't1i»i«(RAS1'«0) 
E50O00(RAS173) 
RI226(RAS176) 
E6000Z()IAS159) 
E6000Z(RAS173) 
E500O0(HAS173) 
R1Zl42(RA$179) 
E5O00R(RAS159) 
E5OO0R{RAS173) 
R3501 (f(ASt82) 
R1226(RAS178) 
E5000R(RAS173) 
E5000R (RAS1 73) 
E5000R (RASI 7^) 
R1226(RAS1Ii2) 
E5000J(RAS183) 
R1226(RAS15Z) 
R3501(RAS158) 
R3501(RAS158) 
R3501(RAS158) 
E5OOOG(RAS190) 
E5000G(RAS190) 
EltlUH(RAS1l«0) 
E'»lM«H(flAS1'»0) 
RI2I*8(RAS186) 
R1Z'i8(ltASl86) 
R60000(RAS173) 
R60000{RAS159) 
E5OO0R(RASI59) 
E5163V<RAS159) 
E7207Y{RAS159) 
E5000R 

E70C10Y(RAS159) 
e6191V(RA5159) 
E6191R(RAS159) 
E6000R(RAS173) 
E5OO0R(RAS190) 
E6000R(RASI59) 
E6000R{RAS159) 
E70O0R(HAS173) 
(RAS30I ) 
E6l8'tV(RASl83) 
E6185V(RA$183) 
E6182V(RASt83) 
E6191Y(RAS183) 
E6189V{RAS183) 
E6000R 

R1226(RAS186) 
E6OO0R(RASI73) 
E6000 (RAS173) 
E6O00R(RA5173) 
E6000ll(RAS173) 
E6000n(RAS159) 
e60O0R(RAS159) 
E600aR(RASI95) 
E60DOR(RASI59) 
E6OO0lt(RAS173) 
E6OO0R(RAS159) 
E6000 

E6183H{RASI73) 
E60000(RAS190) 
E6000G(RAS192) 
E6000H(RAS190) 
e600OE(RAS190) 
E60O0R (RAS1 59) 
E6183H(RAS190) 
E6183U(RAS190) 
E6163H(RAS196) 
E6183H 

E600C«(RASI73) 
E60O0R<RASl83) 
t7193V(RASl83) 
E6l8l¥(RASl83) 
£6187Y(RASI83) 
E6l88v{RASl8l) 
E6l86v(RAS190) 
E719'»V(RAS190) 
E6000tl(HAS190) 
E6188h{RASI73) 
E7I9dH(RAS173) 
e6187H(RASI73) 
E6l6tH(RASt73) 
E6186H<RAS173) 
E7000R(RAS173) 



itSi q 



~~g ?r 



3,300 
3.975 



8.930 
8.930 



2,t»00 
8.013 



34 ,021 
-1.538 



8.910 

8,930 



8.930 
1.670 

-1*1*9 

I*. set 

-3.026 



Bk.ZZO 

-200 

122.300 



118. 088 
6.773 



3<«.6itO 
-1.582 



161.175 
-5,568 



3.380 
17,257 



11.950 
13,100 
2,680 



'♦2.575 
-711 



132,780 
5,760 



67.760 
-^,903 



60.950 
73.500 



16,000 

25,675 

7,275 

-206 

-82 



96,575 
18,900 



wsA-fc90 Mn. yy'ty) aeros-b un-x't otwers 



$657,670 i9Wt,325 S60.862 |I5,6lO 



90. lU 
8,930 
8,930 



8,930 
33,255 

-12,357 



1*11,900 
88.073 
i«,96t 



3ii8,500 
-31.000 



29.500 
7,257 



5.760 
5,780 
8I1.OOO 



31.'t5t 

11,336 

3it,23i» 
74.620 
25,331 
-873 
75,239 
98.687 
107. 495 
58,67^ 
1.7,961. 
1.0,055 
592 
15.1.00 
129,132 
13,600 
11.1*30 
10,1.90 
6,260 
8,1.90 
2.119 
3,398 
-I.8I.7 
32 .939 
32,939 

32.939 
32.939 



651 
651 



8.930' 



31 .*5I ( 



8,930 



11,560 



1.37,882 



30.710 



650 



52. 778,820 S38,131 531,361 533,589 5321.381 



% 90.200 

-700 

3.300 

3.975 

159.000 

84.220 

6.680 

6.680 

-200 

2.400 

8,013 

122.300 

2,400 

750 

118,088 

6,773 

34.021 

-1.538 

90.144 

8,910 

8.930 

8,930 

(21 "•"*' 

^ ' 8.930 

8,930 

8.930 

8.930 

8.930 

8,930 

8.930 

8,930 

8,930 

8.930 

1.670 

33.255 

-449 

4,686 

-3,026 

-12,357 

53,687 

-100 

135.211 

-1,058 

411,900 

88.073 

4.961 

67,760 

-4,903 

34.640 

-1,582 

29,784 

57,575 

348,500 

-31.000 

6.750 

53,375 

3,380 

17.257 

60.950 

73.500 

11.950 

13,100 

2.680 

16,000 

9,490 

25,675 

7,275 

-206 

-82 

42.575 

-711 

161.175 

-5,568 

96.575 

18,900 

29,500 

7.257 

132,780 

5.780 

11.560 

2.175 

1 7,3'.0 

5.780 

5.780 

84.000 

2,900 

617.000 

-350 

437,882 

200,000 

31 .".51 

31 .".51 

31,451 

3l.fc5l 

31.1.51 

11,336 

7^.250 

34.234 

A.620 

25,331 

-873 

75.239 

96.687 

107.495 

58,674 

47.964 

40.055 

592 

15,400 

129,132 

13,600 

1 1 .430 

to. 490 

6,260 

8,490 

2,119 

3,398 

-1.847 

32.939 

32.939 

32,939 

32,939 

32.939 

32.939 

30.710 

30,710 

61 .420 

650 

651 

651 

651 

651 

37,150 



5577.162 541,869 55, 5^.695 



<3)esR0 
*'**WSA-711 



Vehicles Less Motors 








1 Scout 






178 


2 Scout 






179 


3 Scout ♦ H/S A60 






180 


^ Scout 






181 


5 Scout 






182 


6 Scout + H/S A63 






183 


7 Scout 






181. 


8 Scout 






185 


9 Scout 






186 


10 Scout 






187 


11 Scout 






188 


12 Scout 






189 


13 Scout * H/S A66 






190 


lit Scout 






191 


15 Scout 






192 


1^1 Heat Shields 








A58 




ORA 


166 


A59 




SOUIAD 


177 


A61 




SAS-A 


175 


A62 




RAM-C 


171 


A64 








A65 




CAS-B 




A67 








A68 




SM-DM 




A69 thru A7't 








Mod. 5 - Mod. 500 lb 


RCM/ 




valve Assy. 








Mod. 12 - Install Cor 


k. 


Buy 




Winter Kits, 


Revise 




OCEPS, Improve 


X259 




Field Assy. 








Mod. lit - Buy S-Band 


t 


)ther 




Misc. Parts 








Mod. 15 - Mods for SBAS 






Mod. 17 - winter Kits 








Mod. 19 - Change in GFE 






Mod. 23 - Fab. SBASI 


Ha 


nesses 




Mod. 21* - Mods for SBAS 






Algol lie Rocket Moto 


rs 


(Hod. 1.); 


S/N 76 






177 


77 






IV. 


78 






180 


79 






187 


80 






ft 


81 






ft 


82 






ft 


83 






179 


81. 






182 


86 






178 


87A 






ft 


88 






ft 


89 






183 


90 






ft 


91 






ft 


92 






ft 


93 






ft 


Algol Igniters (2) 








Nozzle Housing 









Hod. 18 - Repair Algol Dollies 
Mod. 22-3 Algol Dolly Tires 
Hod. 28 - Algol Storage at AGC 



1 1 Rocket Motors: 




S/K 185 


IV. 


186 


180 


187 


181. 


188 


185 


189 


187 


190 


190 


191 


181 


192 


183 


193 


179 


19". 


178 


195 


170 


196 


197 


197 


182 


198 


188 


199 


191 


200 


186 



SCOUT 
VEHICLE 
MUHBER WSA 



22,278 
22,278 
22,278 
22,278 

22,278 



Castor Igniters (2) 

Hod. 9 - Radiog. Inspect. Castor Nozzles 



X-259 Rocket Motors (Mod. 


U- 




S/N 301 




166 


302 




183 


303 




181. 


301. 




170 


305 




163 


306 




190 


307 




187 


308 




188 


309 




195 


310 




ITS 


311 




18? 


312 




185 


313 




181 


311. 




180 


315 




186 


316 




189 


FW-1.S Rocket Motors (Mod. 


16): 




S/N 2376-1 




182 


2376-2 




181 


2376-3 




191 


2376-1. 




190 


2376-5 




170 


2376-6 




186 



FW-1.S Leak Te 



GRAND TOTAL 



2376-7 
2376-8 
t (Mod. : 



8,720 
2,833 



96,215 



6.411. 



71.. 187 
7"., 187 



ORIGI'MAL PAGE iS 
OF POOR QUALITY 



365 



Figure 108.- NAS1-7199 Proration of Costs. 







PHASE VI 






PWSE VM 




NASA 


NAVY 


A.F. ESKO 


GERMAN 

s 


U.K. 


NASA NAVY 


TOTAL 


s 


5 


S S. 


s 


S S 


S 




1.20,358 












1.1.2 ,636 
1.20,358 


1.20,358 


1.20,358 








1.20,358 
V.2,636 
1.20,358 
1.20 358 


V.2,636 














1.20,358 




1.20,358 


1.20,358 






1.20,358 
1.20,358 
1.20,358 














1.20,358 


1.20,358 








1.20,358 




1.20,358 


Vi2,636 












1.1.2 ,636 


1.20,358 


1.20,358 








22,278 
22,278 


1.20,358 
1.20,358 

22,278 
22,278 
22,278 
22,278 
22,278 
22,278 
22,278 



6,690 
35,649 



1.18,252 

30,948 
-1 ,936 
-4,487 



122,720 
122,720 
122.720 



13.450 

277 

24,000 



96,215 
96,215 

96,215 
96,215 
96,215 
96,215 



96,215 
96.215 



74,187 
74,187 



74,187 
74,188 



74.18 
74,18 



74,188 



75,437 
75,437 
75,437 



75,437 
5.000 



154,107 50,318 50,318 50,318 50,318 



324 108 108 108 



22,278 
133,668 



122.720 
122.720 



96,215 



96.215 
96,215 



96,215 



96,215 



74,188 
74,188 



74.188 



75.437 



5218,935 $646,290 $6,058,147 $2,077,188 $689,719 $641,187 $716,624 $716,624 $646,826 5757.208 513.168.748 



122.720 
122,720 



122,720 
122,720 



122,720 
122,720 
122.720 
122.720 



96,215 



133,668 

6,690 
35,649 

825,000 

30,948 
-1,936 
-4,487 
1,620 
11.056 



122.720 
122,720 
122.720 
122.720 
1 22 . 720 
122.720 
122.720 
122.720 
122.720 
122.720 
122.720 
122,720 
122,720 
1 22 , 720 
122,720 
122,720 
122,720 
8,720 
2,833 

13,450 

277 

24,000 



96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
96,215 
6,414 

7,025 



74,187 
74,187 
74.187 
74,187 
74,187 
74,187 
74,188 
74,188 
74, Its 
74,188 
74,1«8 
74,188 
74.188 
74,188 
74,188 
74,188 



75,437 
75,437 
75.437 
75,437 
75,437 
75,437 
75,437 
75,437 
5,000 



C:-;,;^.:; 



J. ) 











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367' 



ORIGINAL PAGE B 



OF POOR QUALITY, 



-:d- *— C^J CM CM r^ .— 



<C m u o Lu u. 



0,„0"000000000 OOO OOOOOO O OO C 



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3:za:2:3:a.flctn2:zzi:z:si-x;>3:s::3x — 



368 



OF POOR QUALITY 



Figure 109(c).- NAS1-7256 Proration of Costs. 





PHASE 


VII 




















BASIC 


TASK 


SCOPE 


FINAL 


FINAL 








TASK 


PROGRAM 


UK-6 


TASKS 


MODIFICATIONS 


CHANGE 


ADJUSTMENT 


COSTS 


TASK 








NEGOTIATED 




(MOD. 35) 


(Mod. 37) 








VEHICLE 

J 


198 

i ., , 














A 


1 
1 


$1,971,022 


1 




$ 148,514 


$2,119,536 


A 


B 


i 


168, W+7 




$ 9,357 


38,772 


216,576 


8 


C 


1 


200,985 




-35,406 


25,615 


191 ,194 


C 


D 


t 


519,37't 




-427,570 


186,009 


277,813 


D 


E 




1,484,682 






272,061 


1.756.743 


E 


F 




1,360,893 






-126,748 


1,234,145 


F 


Mod. 17 






$ 20,698 






20,698 


Mod. 17 


G 




879.679 






-271.851 


607,828 


G 


Mod. 30 






27,323 






27,323 


Mod. 30 


H.J.K 




1,856,187 




-136,050 


-168,060 


1,552,077 


H, J,K 


Mod. 1 






8,700 






8,700 


Mod. 1 


Mod. 3 






3,010 






3,010 


Mod. 3 


Mod. 6 






7't,600 






74,600 


Mod. 6 


Mod. 7 






48,280 






48,280 


Mod. 7 


Mod. 8 






19.071 






19,071 


Mod. 8 


Mod. 9 






16,100 






16,100 


Mod. 9 


Mod. 10 






31,700 






3 1 , 700 


Mod. 10 


Mod . 1 9 
Mod. 28 






5'+,650 






54,650 


Mod. 19 






2,835 






2,835 


Mod. 28 


L 




459,108 






-44,604 


414,504 


L 


M 




500,000 






-12.047 


487,953 


M 


N 

Mod. 16 




1,118,964 






20,093 


1,139,057 


N 






27,037 






27,037 


Mod. 16 


Mod. 21 






151,626 






151,626 


Mod. 21 


Mod. 29 






5,008 






5,008 


Mod. 29 


P 
R 




308,138 






21,241 


329,379 


P 

R 


S 

Mod. k 






87,441 






87,441 


S 
Mod. 4 


Mod. 14 






34,799 






34,799 


Mod. 14 


Mod. 20 






39,504 






39.504 


Mod. 20 


Mod. 23 






-2,268 






-2,268 


Mod. 23 


Mod. 27 






257, '+79 






257.479 


Mod. 27 


Mod. 33 


lit, 360 




140.609 






140,609 


Mod. 33 


T 




388, 33^+ 






-3.575 


384,759 


T 


Mod. 12 






7,650 






7,650 


Mod. 12 


V 


485,825 








485.825 


V 


Mod. 22 1 i 


41,692 






41 ,692 


Mod. 22 


Mod . 2d 

1 i 1 




1,770 






1,778 


Mod. 26 


W 

Y 1 


34,168 






-7.694 


26,474 


W 


X 

Inc. (Mod. 3^+) 




24,19't 


425.000 




511 


24,705 
425.000 


X 
Inc. (Mod. 34 


Retransfer Per; 






27,037 




-18.927 
$59,310 


8,110 


Retransfer ( 
TOTAL 


TOTAL 


1 


$14,36o 


$11,760,000 


$1,551,359 


$-589,669 


$12,781,000 



369 



ORSGiMAL PAGE SS 
OF POOR QUALITY 



o 



o o o m 
o o o un 

O O r>4 vO 


CMCMtSC-JC-JtslcMNcMCMCJCMCsl 


CM Cvl O LTV O O 

a> o^ o <T\ f^ o 


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LTV 


o o ^ f^ 


vO vO vO \0 ^O ^«0 vO vO vO ^O vO v^ vO 
CMr-JCMCMCMCslcMNr-JCMf-JCMcM 


vO vO CS CS QO 
CM 04 1 1 1 


vD 
CM 

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< 



CM 
<7\ 

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CM 



CM 
CM 



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00 
LTV 



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CM 

cr> 

CM 



CM 
CM 



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CM 



O 
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LTV 






00 
CM 

I 



o 
a: 



J- 

X 



2^ 

ZJ 



CM 

vo 

CM 



CM 
CM 



CM 
0^ 

CM 



CM 
CM 



C 

o 
o 



in 

< 



CM 

CM 



CM 
CTl 

CM 



< 
c/> 

< 



O O O ro 
o o o ur\ 
o O CM vO 



CM (M 



CM CM CM CM 

o^ o> o^ <T\ 
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o o ^ r^ 
o r^vo 

CM 



VO vD 
CM CM 



VO VO 
CM CM 



vO 
CM 



VO 
CM 



O LA O 

o cr> 1^ 

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CM CM 

I I 



o 

J- 

CM 






3 



< 



< 



CM 

o^ 
vo 

CM 



CM 

vO 
CM 



o 






C7) 






< 


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c 


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o 


O 


^— 


x: 




o 




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o 


> 


> 


f- 


Q- 


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* 










o 


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4-) 


1/5 


c 


o 


•« 


Ol 


3 


CM 


* — 


■u 




in 


o 


•o 


(1) 


1- 


O 


o 


o. 


i. 



1_ 

o 

4-> 

o 

CD -M <U c: 4) 

(DO-J-r— LAU>O00»— vOC\-^LAvO— trr\r^(D tf) 

J-lt^oooooo<uo^oocI^ooooo^c^>a^^uo^cJ^J: id 

10^ — .-.-I-.-.- — .-.-.-r-,-Q!:r-i— <j o 

4^ 4-1 c Q- UJ 

in 3 o • u. 

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JJ — ul (D > Q- CM 

in — O — 

a) — — nj "o 4- 

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— o.— cMro-d"iAvD— <U 
(1) O.— CMro-d-LTvvD'^OOCri.— ■— >— r->— ■— "— Om+J <U 

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o 



370 
Fis'jre in(a)-- PRORATION OF CONTRACT NAS1-10000 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TASK 


PHASE IV 


PHASE V 


TASK 


NASA 


NASA (TOTAL S^t. 089.206) 


^kh 


163R 


166 


17OR 


173 


174 


175 


177 


A 


$1 59,^*88 


$ 


$ 


$ 318.938 


$ 


$ 


$ 


$ 


A 


B 


9.158 


2,091 


7.452 


6.478 








930 


B 


C 


24,28't 


28,295 


41 ,262 


28.344 


12,368 




1,972 


23.925 


C 


D 


kit, 2^3 


34.809 


37.246 


32.693 


44,511 


49,795 


35.268 


45,292 


D 


E 


Sit, 885 




10,735 


4.904 




48,455 


3.402 




E 


Mod 26 


















Mod 26 


F 


5'».883 






3.318 










F 


Mod 26 


















Mod 26 


G 


20.150 






1,218 










G 


H 


'*7,070 






2,853 










H 


Mod 26 


















Mod 26 


J 




202.084 




202,084 


148,656 




202,084 




J 


Mod 27 




20,567 




20,567 






20,567 




Mod 27 


Mod 35 


















Mod 35 


Mod UkM 




11.737 




25.000 






17,315 




Mod 44.49 


K 


















K 


L 


26,797 






45.425 










L 


M 


18,86/* 






1,140 










M 


Mod 23 


















Mod 23 


N 


393.185 




393.228 






393.228 




393,228 


N 


Mod 11 


















Mod 11 


P 


















P 


Mod 28 


















Mod 28 


R 


70,08it 


15,060 


29.108 


48,923 


34,622 








R 


Mod 13 


13.361 
















Mod 13 


Mod 33 


















Mod 33 


Mod 36. '+8 


















Mod 36,48 


Mod l^h.kS 


















Mod 44.49 


S 


















S 


Mod 9 






3.948 


11,586 


1,884 






895 


Mod 9 


Mod \k 








19.500 










Mod 14 


Mod 16 


















Mod 16 


Mod 19 








135.850 










Mod 19 


Mod 25 






9.315 












Mod 25 


Mod 32 


















Mod 32 


Mod 37 


















Mod 37 


Mod 39 


















Mod 39 


Mod k2 


















Mod 42 


J 


















T 


Mod 2 




1 ,606 














Mod 2 


Mod 3 








16,116 










Mod 3 


Mod 6 








28,368 










Mod 6 


Mod 15 


















Mod 15 


Mod 20 








6,701 










Mod 20 


Mod 21 


















Mod 21 


V 


if2,6lO 






65.262 










V 


Mod 20 


















Mod 20 


Mod 31 


















Mod 31 


W 


















W 


Mod 29 .'tS 


















Mod 29,48 


Relocation 


















Relocation 


Incentive 




105.285 


105.285 


105.285 


105.285 


105,286 


105.286 


105.286 


Incentive 


Reserve 


















Reserve 


TOTAL 


$979,067 


$421,534 


$637,579 


$1,130,553 


$347,326 


$596,764 


$385,894 


$569,556 


TOTAL 











•- 




ORIGINAL PAGE IS 
OF POOR QUALITY 


5 




1 1 1 

<auoui u. ox 


III 

-1 ^ 


i i 

-Ji: z 


1 iiii iiiiiiiii Illiii ii lUl < 


1 


* 

o 


St 

■"3 


00* 0\ cm" J^ o" .-" m 


P. 
'1 


282.42 7 
4.845 

717,218 

5.775 

47.320 
68.435 
92.259 

$4,372,064 




S 

2.928 

2.740 

1,200 

4,689 
8,162 

65,262 

S84.98I 


5^ 


$159,488 
32.206 

128,405 

79,618 

29,304 
68,414 






J 


161,962 

1.490 
16.116 
28.516 

32.610 
$765,765 


? 


$ 318.938 
4,097 
3.221 

145,013 

145,016 

53.240 
124,353 


■^ s 


OS 


11.604 

10,779 
1.301 

1,290 
1.657 
16.116 

28.516 
65.262 

$1,409,980 


? 


S 
8.123 

1.869 

1,690 

694 
1.618 




5 


10.779 

1.657 
13.143 

28,516 

6.745 

S 75. 705 


00 


$ 318,938 
17.865 
3.114 

207.331 

207,338 

76,121 
177.800 




ss 


1.786 

1.221 
1.656 

26.516 

6.745 
65.262 

$1,162,404 


2 


$ 318.936 
22.027 
23,656 
52,227 
209,562 

207,316 

76,112 
177,781 




ssa 

vO l/\N 

-si 


6,268 

2,433 
1.657 
16.116 
28.367 
28.516 
6.700 

65.262 

10s. 286 
$1,812,636 


5 


S 318,938 

2,829 

27.562 

42.087 

179.122 

179.128 

65.764 
153.604 




4,325 
70,000 

386,217 
7.011 


532 

447 
1.656 

26.516 

65.262 

105.286 
$1,638,286 


CO 


$ 318,938 

9.425 

17,605 

59.539 

196,169 

194.568 

71.441 
166,860 




30,392 

15,532 

386.217 

7,011 




CO 


S 318.938 

6,424 

43,269 

51,317 

184,378 

154,385 

56,680 
132,386 




III 

(A 


3.431 

811 
1.656 

28.516 

65.262 

105,286 
$1,589,675 


^ 


CO 


$239,272 
12.324 
3,259 

137,010 

116.243 

42,675 
136,472 







5.088 

10.779 
961 

12,056 
1.656 
16.116 

31.801 
5824.805 


i 
< 


« 


$159,488 

60,339 

72,716 

26,696 
129.973 






1.356 

10,779 

1,656 
16,116 

28.512 
31 .801 

559 7. 781 


o 


s 


oa OWO 0\ 0\ so rsi.^ 




52,326 

386,217 
7.011 


1.997 
1.656 
16.116 
28.367 
28.516 
6.700 

21,801 

105,266 
$1,649,964 




? 


$ 

112.663 







9.258 

1,656 
68.502 

$242,608 


1 


20. 


. 5 






37.912 
$43,157 


53 


$ 
5.665 

$5,665 


<r> 


1 318.938 

7.568 

32.292 

41 .959 

2.255 

150.371 




42.508 

386.217 
7.011 


36.325 
16.755 

1,657 

65,262 

105.286 
$1,214,424 


z 


S 

25.673 
4.173 

35.712 






00 

.0 


ss 


S 

7.075 
34.616 

1.132 




42.508 

386,217 
7.011 


20.412 

1.656 

105.286 
$605,913 


« 


VO .O ^0 

■o -o -0 

ill 

<ICQUQUJ U. OX -1 


ill 


.jj. 


Hod 28 
R 

Mod 13 

Hod 33 

Mod 36,48 

Mod 44.49 
S 

Mod 9 

Mod 14 

Mod 16 

Mod 19 

Hod 25 

Hod 32 

Mod 37 

Hod 39 

Mod 42 
T 

Mod 2 

Hod 3 

Hod 6 

Mod 15 

Hod 20 

Hod 21 
V 

Mod 20 

Mod 31 
W 

Mod 29.48 
Relocation 
Incentive 
Reserve 

TOTAL 



372 
Figure 111 (c) .-PRORATION OF CONTRACT NAS1-10000 



0RIG!h3AL PAGE IS 
OF POOR QUALITY 



TASK 


PHASE VII 


PHASE VIII 


TOTAL 


TASK 


A 


$ 


$ 


$ 3,907.116 


A 


B 


50,837 




378.095 


B 


C 






412,882 


C 


D 






641.175 


D 


E 


'♦.3'.3 




3,320.820 


E 


Mod 26 


277.200 




277.200 


Mod 26 


F 






2,062,687 


F 


Mod 26 


37.784 




37.784 


Mod 26 


G 






771,154 


G 


H 






1,801,184 


H 


Mod 26 









Mod 26 


J 






749.000 


J 


Mod 27 






252.335 


Mod 27 


Mod 35 






245,000 


Mod 35 


Mod M+.i+g 






54,052 


Mod 44.49 


K 


15,948 




31 ,896 


K 


L 


336,201 




815.942 


L 


M 






500,000 


M 


Mod 23,49 






221,548 


Mod 23.49 


N 






4,290,410 


N 


Mod 11 






35,055 


Mod 11 


P 


287,272 




569,699 


P 


Mod 28 






4.845 


Mod 28 


R 


111,809 




645.000 


R 


Mod 13 


409,918 




1,199,924 


Mod 13 


Mod 33 


350,000 




350,000 


Mod 33 


Mod 36, /t8 




235.000 


235.000 


Mod 36.48 


Mod kh,kS 


108,185 


-75,000 


33,185 


Mod 44,49 


S 








S 


Mod 9 


47.051 




83,671 


Mod 9 


Mod 14 


57,428 




76,928 


Mod 14 


Mod 16 


29,426 




41 ,469 


Mod 16 


Mod 19 






135,850 


Mod 19 


Mod 25 






10,515 


Mod 25 


Mod 32 


10.125 




60,013 


Mod 32 


Mod 37 


12.424 




128,664 


Mod 37 


Mod 39 


108,153 




210,856 


Mod 39 


Mod kZ 


-100 




-100 


Mod 42 


T 


193,451 




216.040 


T 


Mod 2 







23.139 


Mod 2 


Mod 3 


92,003 




234,074 


Mod 3 


Mod 6 







113,469 


Mod 6 


Mod 15 


142,564 




427,720 


Mod 15 


Mod 20 







26,801 


Mod 20 


Mod 21 


13,490 




26,980 


Mod 21 


V 






816,483 


V 


Mod 20 


6.405 




6,405 


Mod 20 


Mod 31 


-641 




-641 


Mod 31 


W 









W 


Mod 29,48 


209,7)5 




209,7)5 


Mod 29,48 


Relocat ion 


1,976 




1,976 


Relocat ion 


1 ncent i ve 






1 .474,000 


Incentive 


TOTAL 


$2,912,95'7 


$160,000 


$28.T67.00S 


TOTAL 



PHASE 



ORfGfNAL PAGE m 
OF POOR QUALITY 



373 
Figure 112.- Proration of Other Contracts. ('♦gO-Funds only.) 
V AND PRIOR VI 



NAS-1 


NASA 




NAVY 


A.F, 




NASA 




NAVY OTHERS 


VII & SUB. 
$ 


TOTAL 


4664 


$3,123,553 


$2 


,180,438 


$ 742, 


740 


$ 9.224 


$1 


,388,414 $ 


$ 7.444.369 


5883 


2.435.942 




609,264 


310.891 






34.501 




3.390.598 


6868 


1.189.569 










22,244 








1,211.813 


7102 












528.525 








528.525 


10481 






6,355 










160.397 


. 154,042 


320,794 


10482 


181 










41 ,938 




30, 040 (') 14, 433 


115,077 


201 ,669 


10483 


89.694 










30.088 




11,368(1)11.232 


208,668 


351 ,050 


10484 












51.846 




24,259 28,249 


424.707 


529,061 


10500 












678,693 






370,589 


1,049,282 


11000 












40.800 






10.448,125 


10.488,925 


11859 












44.665 








44.665 


11867 












119.325 








119,325 


13100 
















286.147 


3.563,112 


3.849.259 


16520 












83,490 
$1 ,650.838 


$1 






83.490 


TOTAL 


$6,838,939 


$2,796,057 


$1,053,631 


.935,126 $53,914 


$15,284,320 


$29,612,825 



(1) Includes P-76 (AF) S-179. 



Figure 113.- Phase VI R £■ D - Propulsion Prorations. 







CONTRACT 






VEHICLE 


NAS1-10481 


NASl-10482 


NASI -10483 


NASI -10484 


TOTAL 


178 


$ 3.006 


$ 4.811 


$ 3.744 


$ 6,180 


$ 17.741 


179 




6.536 


3.880 




10.416 


180 




4.811 


3,744 


1,654 


10.209 


181 




4,811 


3,744 


10.112 


18,667 


182 




4,811 


3.744 


3,772 


12.327 


183 




4,811 


3.744 


1,654 


10,209 


184 




4.811 


3.744 


10,112 


18,667 


185 




4.811 


3.744 


8,025 


16,580 


186 




4,811 


3,744 


10,112 


18.667 


187 




6.536 


3,744 


1.725 


12.005 


188 




4,811 


3,744 


10.112 


18.667 


189 




6,536 


3,744 


6.340 


16.620 


190 




4,811 


3,744 


10.112 


18.667 


iai 




4,811 


3.880 


10,137 


18-878 


192 




13,882 




14.307 


28,189 


Sustaining 


157.391 


68.865 


43,154 


19.249 


288,659 



TOTAL 



$160,397 



$155,276 



$ 95,842 



$123,603 



(1) Includes P-76 (AF) S-179. 
(2)Does not include Phase V. 



$535,118 



374 



Figure 1 14.- CONTRACT NAS1-11400 ESTIMATED PRORATION OF COSTS 



ORIGIMAL PAQS IS 
OF POOR QUALITY 



ITEM 

Castor I lA 
S/N 382 
383 

>H':384 

*.V385 

.v*386 

«.387 

390 

391 

392 

393 

394 

395 

911 

912 

913 

914 

Castor I lA 

455- 

455- 

455 

455 

NOTE: MOD 



SCOUT 

VEHICLE 

NUHBER JOB ORDER 



Rocket Motors w/Nozzles: (TX354-IIA) 



(Less N02zles)-Sandia 

(Less Nozzles)-Sandia 

(Less Nozzles)-Sandia 

(Less Nozzles}-Sandia 



(Case Only/MOO l4)Mtr. 
(Case Only/MM 14)Test 
(Case Only/MOO l4)Mtr. 
(Case Only/MOO l4)Htr. 
Nozzles Only: 
03 
05 
07 
08 



S-195 
S-196 
S-202 
S-192 
* 

S-203 
S-194 



808 

809 
810 



193 
200 
198 
201 



E 71 952 
E7196Z 
E7202Z 
E6192Z 
E7204Z 
E7203Z 
E7194Z 
E7000Z 
E7193Z 
E7200Z 
E7198Z 
E7201Z 
E7000Z 
E7000R 
E7000Z 
E7000Z 

E7202Z 
E72052 
E7204Z 
E7203Z 



14 ($202,161 total credit for not loading 



Antares I 

S/N 401 

402 



Rocket Motors: (X259B4) 



403 (AEDC Test) Case 205 

404 

405 

406 

407 

408 

409 

204 (Case Only/MOO 14)Mtr 

208 (Case Only/MOD 14)Mtr 

211 (Case Only/MOD 14)Mtr 

209 (HE Test/MOD 14) 

212 (Case Only/MOO 14)Mtr 
214 (Case Only/MOO 14)Mtr 



S-191 
S-179 



MOO 5 
NOTE: 



E619IZ 
E6179Z 
E7000Z 
E7197Z 
E7193Z 
E7196Z 
E7194Z 
E7200Z 
E7198Z 
E720OZ 
E7201Z 
E7202Z 
E7000R 
E7204Z 
e6192Z 
E7199Z 
E7000R 
E7000R 
E7000R 
MOO 14 ($120,713 total credit for not loading 9 
MOD 22 Antares IIB Igni ters/M26(L/L) E7000Z 

MOD 28 Antares IIB Igniters E7000Z 

MOO 29 Price Reduct ion/M28 E7000Z 



410 
411 
412 

413 
414 



S-197 
S-193 
S-196 
S-194 
S-200 
S-198 
* 

S-201 
S-202 
(a) 



S-192 

215 (Case Only/MOO 14)Mtr. 415 S-199 
203 (Nozzle Def lection/MOO 14) Mtr. 417 

216 (HE Test/MOD 14) 
Hydrotests 



Altair IIIA Rocket Motors: (TEM640) 
Design Tests EOl-ElO 
S/N Ell 77% F Alt. Test ^ T.C. 
E12 77% F Alt. Test (5> RPL 
EI3 W/Case 008 S-187 

E14 W/Case 009 S-189 

EI5 W/Case 014 S-195 

EI6 W/Case 020 S-194 

El 7 W/Case 013 S-197 

EI8 W/Case 012 S-196 

EI9 W/Case 027 S-193 

E20 W/Case 026 S-200 

E21 W/Case 024 S-179 

E22 W/Case 023 NRL 

(Case Only 010/Mod.l4) U.T.C. 
(Case Only Oil/Mod. 14) U.T.C, 

(Case Only 01 5A/Mod.l4)H.E .P.Test(^) 
(Case Only 025/Mod.14) U.T.C.-N.F.W. 
(Case Only 028/Mod. 14) (Motor E29) 
(Case Only 029/Mod .14) (Motor E30) 
(Case Only 030/Mod .14) (Motor E3t) 
E23 Nozzle/Igniter w/atcii.hdwe. 5Cs .P/Fi t . 
E24 DITTO NRL 

E25 DITTO 

E26 DITTO 

E27 DITTO 

E28 DITTO 

(Nozzle Only) 004 (Motor E36) NRL 
(Nozzle Only) 014 (Motor E34) NRL 



1 Altair II lA Nozzle 

Mod . 3 Too ling 

Mod. 16/17 (Dual. Firing/M24) 

Mod. 18 Finish 7 Nozzles, Nos. 109-115 

Mod. 19 (Spec. Change) M24 

Mod. 20 (Inspect S/N Oil) M24 

Mod. 27 (Altair III Hardware) (Case) 

Mod. 23 (Altair III Igni ters/M26) 



S-191 



(c) 



E7000R 
E7000R 
E7000R 
E6187Z 
E61 89Z 
E7195Z 
E7194Z 
E7197Z 
E7196Z 
E7193Z 
E7200Z 
E6179Z 
E8006Z 
E7000R 
E7000R 
E7000R 
E7000R 
E7I98Z 
E6I92Z 
E7000Z 
E7201Z 
E8006Z 
E6192Z 
E7203Z 
E7202Z 
E7000Z 
E8OO6Z 
E8OO6Z 
E6I9IZ 
E7000V 
E7000R 
E7000Z 
E7000R 
E7000R 
E7000Z 
E7000Z 



PHASE VI 




PHASE VII 






NASA NAVY 


NASA 


NAVY 


U.K. 


TOTAL 


5 $ 


$ s 

97,872.00 
55.000.00 


97.872.00 $ 




$ 97.872.00 
97.872.00 
55.000.00 


55,000.00 


55.000.00 
97.872.00 
97,872.00 
97.872.00 

97.872.00 
47.331.75 
47.331.75 
47,331.75 
47,331.75 

42,872.00 
42,872.00 


55.000.00 
97,872.00 

42,872.00 
42,872.00 


97,872.00 


55,000.00 
55,000.00 
55,000.00 
97,872.00 
97,872.00 
97,872.00 
97,872.00 
97,872.00 
97,872.00 
47.331.75 
47.331.75 
47.331.75 
47.331.75 

42,872.00 
42,872.00 
42,872.00 
42,872.00 


tors has been prorated over each 


MOO-14 motor listed 


above . ) 






77,600.00 








77,600.00 


77,600.00 


77.600.00 

77.600.00 
77.600.00 
77.600.00 

64,187.45 
64,187.45 
50,967.45 


77.600.00 

77.600.00 
64.187.45 

64,187.45 


77,600.00 


77,600.00 
77,600.00 
77,600.00 
77,600.00 
77,600.00 
77,600.00 
77.600.00 
77.600.00 
64,187.45 
64.187.45 
64.187.45 
50,967.45 
64.187.45 


64,187.45 


64,187.45 

50.967.45 

7.858.00 


64,187.45 




64,187.45 
64,187.45 
64,187.45 
50,967.45 
7.858.00 


59 's has been prorated over each 


MOO-14 motor 1 isted 
36.550.00 
2,715.00 
-1,596.00 

300,205.00 
46,263.00 
46.263.00 


above . ) 




36.550.00 

2.715.00 

-1.596.00 

300,205.00 
46.263.00 
46,263.00 


34.501 .00 








34,501.00 


34.501 .00 


34.501 .00 

34.501 .00 
34.501 .00 


34.501 .00 
34.501 .00 

34.501 .00 




34,501.00 
34,501 .00 
34,501 .00 
34.501 .00 
34,501.00 
34,501 .00 
34,501 .00 


34.501 .00 


12,724.00 
12,724.00 
12.724.00 
12,724.00 


38.469.00('') 


12,724.00 


34,501 .00 
38,469.00 
12,724.00 
12,724.00 
12.724.00 
12.724.00 
12.724.00 


12.724.00 


13,130.00 






12.724.00 
13,130.00 




991 .00 


991 •OO*''' 




991 .00 








991 .00 


991 .00 


991.00 
991.00 
991 .00 


8.016.00!^! 
8,016.00*"' 




991.00 
991 .00 
991 .00 
991 .00 
8,016.00 
8,016.00 


5.357.00 


2,100.00 
23.000.00 

9.590.00 
16.664.00 

4,600.00 
19,800.00 
17,103.00 






5,357.00 
2,100.00 

23,000.00 
9,590.00 

16,664.00 
4.600.00 
19,800.00 
17,103.00 


$151,959.00 $245,003.45 


$2,181,936.25 


$843,245.35 $188,196.00 


$3,610,340.05 



A Inventory . 
v.-v-These motors were purchased by Sandia, but were returned to Scout. 

(a) NASI-I25OO-RM4. 

(b) For mi Program, Phase VIII time period. 

(c) For motors E31 , E32, E33 , E38, E37. E35 and #115 is in Spares, 
L/L Line Loss Purchased. 



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376 



ORIGSNAL PAGE SS 
OF POOR QUALITY 



Figure 116.- Contract NAS1-1'*200 - Proration of Costs. 



CONTRACT PHASE 


VI. NAVY S-192 


PHASE VI & SUBSEQUENT 
$ 


TOTAL 


2nd Stagte 


$ 


M-6 




339,800 


339,800 


-9-13 




1.'*56.'t2^ 


1, '+56, 1+23 


M-8 




50, if 18 


50 ,'+18 


M-l't-15 




7'+8,06't 


7'+8,06'+ 


3rd Stage 


$ 15,260 


2'*2.815 


258,075 


M-1 




'+0,629 


'+0,629 


M-3 




1,080 


1.080 


M-5 


1'*0,03't 


1.725.7'+9 


1,865,783 


M-1 7 




l8l.5'+7 


l8l,5'+7 


'*th Stage 


93.115 


'♦72,010 


565,125 


M-2 




261 ,6'+5 


261 ,6'+5 


M-'t 




683,73'+ 


683,73'+ 


M-7 




'♦0,559 


1+0,559 


M-18 




1,310,039 


1,310,039 


M-20 




256,600 


256,600 


M-21 




101,505 


101,505 


1st Stage 









M-10 




2,216,1+45 


2,216,4+45 


Schedule Changes 




258,510 


258,510 


TOTAL 


$2't8.1+09 


$10,387,572 


$10,635,981 



Figure 117-- Contract NAS1-15000 



PHASE VI 



PHASE VII 5. SUB. 



TASK 

A 
B 
C 
D 

E 
F 
G 
H 
J 
L 
M 
N 
P 
R 
S 
T 

V 
W 
X 
Y 
Z 



M-19 



NAVY S-192 


HARDWARE SUPPORT 




$ 


$ 


$ 7,811,260 


4,239 




201,744 


24,326 




202,325 
423.399 


14,236 




3.468.928 
3.598.302 
1.554.754 


73.920 


5,242 


4.116.334 

304.225 

1.126.747 


50,968 




1.415.482 

9,596.587 
1.052,502 


113.506 




2,902,714 
250,317 


35.184 




2,385,846 


18,043 




55,741 




43,503 


1,246,744 


100.000 




500,000 
72,611 


70,491 




15,223,354 
84,939 



TOTAL 



$504,913 



$48,745 



$57,594,855 



377 



ORIGINAL PAGE IS 
OF POOR QUALITY 



J.O.(VI) 



E6192R 
E6192H 
E6192B 
E6192H 

TOTAL 



Figure 118.- NASl-15100 Contract Proration. 



PHASE VII & SUB. 

$ 585,863 
3,390,285 
9,300,12if 

(19,911) 
(48,589) 



TASK 


PHASE VI 


J 


$ 


M 


2,508 


R 


118,094 


66r 


(22,005) 


83 H 


(19,911 


1118 


(56,438) 


119H 


(19.740) 



$120,602 



$13,276,272 



TOTAL 

$ 585,863 
3,392,793 
9,418,218 
(22,005) 
(39,822) 
(105,027) 
(19,740) 



$13,396,874 



The Scout participated in foreign programs from many European countries 
including ESRO (name cfianged to ESA at later date). The largest foreign 
reimbursable Scout program was with Italy. (Note description on page 230.) 
Table CVIII itemizes the funds received and Table CIX lists the work break- 
down structure used for financial requirements. 



TABLE CVIII - FOREIGN REIMBURSABLE AUTHORITY 






A EROS 


ITALY 


UNITED 


KINGDOM 




Fiscal Year 


UK- 5 


UK-6 


TOTAL 


FY 74 


$2,640,000 




$ 58,325 




$ 2,698.325 


FY 74 (STS DIRECT) 






664,525 




664,525 


FY 75 


1,011.995 




65.000 


$ 98,000 


1 ,1 74,995 


FY 75 (STS DIRECT) 


318,533 








318,533 


FY /6 


24,617 




11,308 


2,292,553 


2.328.478 


FY 76 (STS DIRECT) 


14,707 




73,431 




88,138 


FY 77 


20,419 


$ 183,363 




11,200 


214,982 


FY 77(STS DIRECT) 


110,000 








110,000 


FY 78 


629 


479,647 




1,076,760 


2.173,036 


FY 78 (STS DIRECT) 




202,629 




10,000 


212,629 


FY 79 




63,889 




114,266 


178,155 


FY 79 (STS DIRECT) 




37,042 




228,335 


265,377 



TOTAL 



$4.030.900 $1.076.570 $872.589 $4.447.114 $10,4277l7r 



FY 71 & Prior 

FY 72 

FY 73 

FY 74 

FY 75 

FY 75 (STS DIRECT) 

FY 76 



TABLE CIX - TRUST FUNDS 



ESRO 



IB 



IV 



$2,252,771 



210,656 



$1,550,000 
800,000 
331.834 



911.167 



United 
Kingdom 

x-4 



$ 50,000 

1,345,834 

1,695,786 

680,597 

76,988 



Italy 



TOTAL 



$1,008,147 $ 4,810,918 

850,000 

1,262,647 2,939,854 

1,695.786 

653,600 1,544,853 

76.988 

911.167 



$2,463,427 $3,593,001 $3,848,744 $2,924,394 $12,829,566 



TOTAL 



TOTAL FOREIGN REIMBURSABLtS 



378 



TABLE CX - ESRO IB FINAL COSTS (S-172) 



1 . Vehicle Procurement 

Vehicle Hardware 

Motors 

Certification and Processing 

Tool ing 

Spares 

2. Transportation 

3. Launch Services 

GSFC 

KSC 

LTV/WTR 



$1,023,510 



$46 2, if 13 

319,137 

164,921 

28,347 

48,692 



6,287 

17.813 

134,877 



20,000 
158,977 



4. Project Management and Engineering Support 815,803 

Program Management 205,261 

Systems Engineering 144,302 

Reliability 98,732 

Pref light Planning 21,032 

Pay load Coordination 38,424 

Configuration Control 49,035 

Data Reduction 69,453 

R&D ^*2 

LTV-lncentive Award 106,250 

Spares Administration and Replenishment 82,902 

5. DOD Contract Administration 15,960 

6. Travel and Project Management 81 ,605 

7. Range Services 347,572 

8. Overhead 38,192 



TOTAL $2,501,619 



379 



TABLE CXI - ESRO-IV FINAL COSTS (S-185) 



1. Vehicle Procurement 

Vehicle Hardware 

Motors 

Certification and Processing 

Too 1 i ng 

Spares 

2. Transportation 

3. Launch Services 

LTV/WTR 

Photography (included in A.F.) 

Complex - GSE and Maintenance 

h. Project Management and Engineering Support 

Program Management 

Systems Engineering 

Rel iabil ity 

Pref light Planning 

Mission Integration 

Configuration Control 

Data Reduction 

LTV Incentive Award 

5. DOD Contract Administration" 

6. Others 

Travel 

LRC Project Support 

7. Range Services 

GSFC 
KSC" 
DOD 

8. Overhead 



$1,269,009 



$581,617 

387,048 

183, 25^* 

52,804 

64.286 



393,228 

2,000 

37.500 



318,938 

151,969 

184.566 

16,066 

45.612 

67,762 

45,309 
105,286 



20,000 
49,600 



37,221 

25,824 

779,465 



20,000 
432 , 728 



935.508 



23,646 
68,600 

842,510 



60,872 



TOTAL 



$3,653,873 



"Headquarters Direct 



380 



TABLE ex. I I.- AEROS-B FINAL COSTS (S-186) 



Vehicle Procurement 

Vehicle Hardware 

Motors 

Certification and Processing 

Tool ing 

Spares 

Mission Pecul iar 



$1,^29.195 



$587,837 

itOO,758 

2 76,687 

86,088 

76,467 

1.358 



2, Transportation 

3. Launch Services 

Vought/WTR 't2'»,650 

Photography 2,000 

Complex - GSE and Maintenance 37,500 

A. Project Management and Engineering Support 

Program Management 
Systems Engineering 
Reliability (F & W) 
Pref 1 ight Planning 
Mission Integration 
Configuration Control 
Data Reduction 
Vought - incentive 

5. "D.O.D. Contract Administration 



Others 

Travel 20,000 

Administrative Expenses 87,^20 

'^Depreciation 9'»,242 

*GSFC-Management Support A5,275 

Range Services 

*KSC (118) 19,673 

GSFC (95) by LRC 118,583 

D.O.D. 6^0,350 





310.900 




196,477 




155.637 




14, 495 




4,474 




61,857 




43,086 




100.000 


LRC - 


■ 25,022 


GSFC - 


■ 1,067 



8. *Agency Overhead 



19.981 
464.150 



886.926 



26,089 



246,937 



778,606 



TOTAL 



179.016 
$4,030,900 



*Headquarters Direct 



381 



TABLE CXI I I - UK-X4 FINAL COSTS (S-188) 



1. Vehicle Procurement 

Vehicle Hardware 

Motors 

Certification and Processing 

Tool ing 

Spares 

Miss ion Pecul iar 

2. Transportation 

3. Launch Services 

Vought/WTR 

Photography 

Complex - GSE and Maintenance 

k. Project Management and Engineering Support 

Program Management 
Systems Engineering 
Rel iabi 1 i ty 
Pref I ight Planning 
Mission Integration 
Configuration Control 
Data Reduction 
Vought - Incentive 

5. DOD Contract Administration" 

6. Others 

Travel (105) 

Administrative Expenses (105) 

7. Range Services 

KSC by LaRC (Ok) 
^VKSC (118) (15,^75)01,(4,498)03,(2,300)04 
GSFC (95) -'^Subauthorization) 
DOD 

8. Agency Overhead" 



$1,357,910 



$579,595 

402,074 

229,824 

62,804 

77,5^^ 

6,069 



424,650 

2,000 

37,500 



330,943 

213,125 

166,448 

22,022 

13,218 

63,963 

40,821 

100,000 



20,000 
74,400 



4,140 

24,573 
23,000 

829,897 



20,000 
464,150 



950,540 



25,419 
94,400 

881 ,610 



54,715 



TOTAL 



$3,848,744 



-Headquarters Direct 



382 



UK-5 was a cooperative space mission between the United States and the United 
Kingdom. Phase VI included five cooperative missions; S-180-French, S-lBl-Qerman, 
S-183 and S-187-United Kingdom, and S-190- Italy. However, the UK-5 (S-I87) was 
unique in that prior to launching from the United States, the United Kingdom 
requested an equatorial launch from San Marco Range. The UK funded this request 
which is itemized in table CXIV. 



P.R. NO. 



PHASE VI 



ORDER NO 



TABLE CXIV - UK-5 REIMBURSABLE EXPENDITURES, FY 197't. 
ITEM J.O. NO. DESCRIPTION 



-01 HARDVWRE 



MISSION PECULIARS (01 -Cl) 



4-2*+- 74 






HI951715 




R9305 


5-23-7^ 






H1951715 




R9305 


5-3-7't 






H2136375 




R9305 


5-23-1^ 






H2136377 




R9305 


5-23-74 






H213637 




R9305 


5-23-74 






H2136379 




R9305 


5-23-74 






K0044422 




1^9305 


11-22-74 






L0480564 


001 


E6I87X 


4-16-75 






HI951715 


004 


E6I87X 


66. 


000 


.449 


NASI-I250O-X 


248 


E6I87X 


6600.0449 


NASI-I250O-X 


858 


E6187X 



-02 SUPPORTING ACTIVITIES 

MISSION REQUIREMENTS (02-04) 
6600.0449 NASI -1 2500- 12-JlO 



Ship Motors to San Marco 
Ship Motors to San Marco 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Handcarry Guidance Comps. 
Ship Miscellaneous Items 



to S/M 



MISSION PECULIARS SUBTOTAL 
HARDWARE SUBTOTAL 



372 E6I87-I LTV Support to UK-5 



OBLIGATION 



7,900.00 

40,000.00 

508.80 

961.73 

816.15 

774.60 

909.48 

18.01 

50.00 

4,528.00 

30.00 

56.496.77 
56,496.77 



1,828.23 



SS DIRECT 



Ital ian Range Costs 



664.525.00 
MISSION REQUIREMENTS SUBTOTAL $ 666.353.23 
SUPPORTING ACTIVITIES SUBTOTAL $ 666.353.23 
PHASE VI SUBTOTAL 
FY 1974 TOTAL 



$ 722.850.00 



$ 722,850.00 



383 



TABLE CXIV Concluded - UK-5 REIMBURSABLE EXPENDITURES, FY75 6 FY76. 



P.R. NO. 
-01 HARDWARE 



ORDER NO. 



ITEM J.O. NO. DESCRIPTION 



OBLIGATION 



MISSION PECULIARS (01-04) 



4-22-75 

4-22-76 

n-8-74 

11-22-74 

8-14-75 

1-17-76 

3-1-9-75 

8-1-75 

12-19-75 

12-19-75 

12-6-74 



H1951715 

L0276437 

LO276663 

LO276662 

L02 76662 

LO 2 7643 7 

K0044714 

K004477 

K0480557 

K0480541 

KOO44526 



-02 SUPPORTING ACTIVITIES 

MISSION REQUIREMENTS (02-04) 

66,000.449 NASI -12500-1 2- J10 
66.000.443 NASI-I25OO-I2-JIO 



-02 SUPPORTING ACTIVITIES 



MISSION REQUIREMENTS (02-04) 
6600.0449 NASI -1 2500- 12-JlO 



003 


E6187X 


004 


E6187X 


001 


E6187X 


001 


E6I87X 


002 


E6I87X 


002 


E6187X 


001 


E6I87X 


006 


E6I87X 


001 


E6I87X 


001 


E6187X 


001 


E6I87X 



371 E61871 
307 E6187I 



FY 1976 



Ship Motors to San Marco 
Ship S-I87 to San Marco 
Ship Hydroset for Spacecraft 
Return Vans to U.S.A. 
Return Vans to U.S.A. 
Return Vans to U.S.A. 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 
Ship Miscellaneous Items 

MISSION PECULIARS SUBTOTAL 

HARDWARE SUBTOTAL 



LTV Support to UK-5 
LTV Support to UK-5 



$ 


6,451.48 




18,360.24 




622.77 




242.00 




245.78 




1,261.19 




294.80 




329.36 




155.72 




22.20 




604.84 


$ 


28,590.38 


$ 


28.590.38 



22,434.00 
13.975.62 



MISSION REQUIREMENTS SUBTOTAL $ 36. 409.62 

SUPPORTING ACTIVITIES SUBTOTAL $ 36. 409.62 

PHASE VI SUBTOTAL $ 65.000.00 

FY 1975 TOTAL $ 65.000.00 



ekk E6I87I LTV Support to UK-5 $ 11,307-15 

MISSION REQUIREMENTS SUBTOTAL $ 11.307-15 



SS DIRECT 



Italian Range Costs $ 65,399-00 

CRA HITS Support 8,032.00 

OSS DIRECT SUBTOTAL $ 73.431-00 



SUPPORTING ACTIVITIES SUBTOTAL $ 84,738.15 
FY 1976 TOTAL $ 84,738.15 



384 



TABLE CXV - UK-6 MAY 1, I98O ESTIMATED COSTS, 
Vehicle Procurement 



Vehicle Hardware (y) 

Motors (Z) 

Certification & Processing (H) 

Tooiing (V) 

Spares (M) 

2. Transportation 

3. Launch Services 

LTV/WTR Field Maintenance (N) 
LTV/WTR Launch Services (N) 

4. Project Management & Engineering Support 

Program Management (A) 

Systems Engineering (E) 

Reliability & Training (F, K) 

Pref light Planning (C) 

Mission Integration (B) 

Configuration Control (G) 

Data Analysis (D) 

LTV - Incentive (W) 

Spares Administration & Replenishment (L) 

R&D (R) 

Mission Peculiars, Supporting Services (j) 
LTV/SPO (p) ' 



$973,613 

564,973 

303,147 

80,350 

69,981 



175.332 
286,402 



399,273 
241,972 
235,574 

34.636 

68,013 
104,633 

64,280 
100,000 

48,326 

216,256 

105,553 
46,978 



$1,992,064 



23,514 
461,734 

1,665,494 



5. D.O.D. Contract Administration (Q) 

6. Project Management and Support 

Travel: (U) 

LRC 

Via ! lops 
Management: 

LRC 

Wal lops 

GSFC 
Depreciat ion 

7. Range Services (|) 

WFC 
GSFC 



8 . "Agency Overhead 



31,900 
43 

129.300 

120,134 

10,000 



TOTAL 



31 ,943 
259,434 

63,499 



86,400 
75,000 



NOTE: 



Based on processing of 42% NASI -12500 and 58% NASI -15000 
---Includes Wallops (S $108,159, LaRC $145,800 



40 , 049 
354,876 



161 ,400 



306.996 
$5,006,127 



385 





1^ 


CM 


_l 


VO 


-;r 


<. 


O 


c 


1- 


O 


rr\ 


o 






1- 


IS\ 


-T 



^ Lnoo vo 

O cv^ CM o 
-=»" vO lA T- 
o O O O 



O C O O O C3 



C^ '£}'-- CM r<-» CM — ^ 

r^-a- Lr\ c <r> »- irv 

1*^ if> 2 *^ f^ f*^ o 

u^cM o >- ^ o o 

. . 

o o o o o 



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• 3" irvcx) CTl 

O -3- -^ O C 
ro C .- ^ C 

C C C C o 



O 
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ir\ La 

^ LTiOO \o 

<3 CO cm o 

-^ vO urv .— 

o O o O 

• • • . 

o c c c 



1^ 

CM 
C 
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-3- 
C 



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vo LTV 
<T\O0 

(r\ o 
c o 

CD c 



CM CO {vg 

O .^ O 

CM CM CM 

-- C c 

o d d 



CM 

-a- 

CM 
O 



CO 

to 



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o 
o 

CO 






o 
o 

(/) 

c 
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LTV 



cx> o Lr\ vO 

IJ^ O O CD 

• • • , 

»- o o o 



LTV 

c 
c 



iO o <N tn 

g -3- CO 

^ O CO 

o d d d 



CO 
lA c<-> 

vO o 

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VO CM 

cx) <» o~\ 

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VO 
r^ 
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CM 

CM 



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C 
C 



c 
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5 ° 



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■I-I 

c 
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CJ 



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DC 00 L. CJ 
— • C3 t3 :2 



1- 

o 



V 

m 

1. 

c 
O 



•J <_' 
<u oe c_) 

1- (D U- 

Q._i :2 



(U 

o 

> 
1- 

CO 

— OJ 

— O CJ > o o 

> u. o Qc (D q: ll 
•- to u. (D i_ nj (o 
o ts s -J I- _j d 



o d 






f 



CM 
C 





1. 








tn 


OJ 








i- 


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<u 


1. 








4J 


0) 








1- -a 


3 








(IS to 


cr 








2- <" 


-o «J 




CJ 




D- x: 


ro oc 


CJ 


li- 




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0) (D 


U. 


to 




(D O (U 
(U u. > 


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cn 


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J3 
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C 



386 



Table CXV presents the data for the only Phase VII foreign reimbursable Scout 
mission. It was very well published because it was the one-hundredth Scout 
launch. This culminated in a NASA-wide banquet, a commemorative coin, and a 
full-scale nonflightworthy Scout in the newly established Aerospace Smithsonian 
Museum. 

Table CXVI shows the funding over a typical five-year period. This depicts 
the funding requirements for a Scout mission. 

San Marco, the largest of the Scout foreign reimbursable programs and 
previously mentioned, had all commitments approved by telegram from Italy. 
These requirements were contracted to Vought Corporation on a task- type 
contract referred to as "J." Tables CXVII and CXV I I I itemize the tasks for 
contracts NASl-10000 and NASl-12500. These cover part of two sections of the 
program (San Marco C and D) . Table CXIX is a typical example of the U.S. 
report to Italy on San Marco "C" and Table CXX is a typical Scout Project 
Office report on San Marco "D" to NASA Headquarters. 



TABLE 


CXVII - SAN MARCO 


WA 3334 




TASK CODE 


CRA AUTHORITY 


AAB 


SG/3501/09/N-2 


AAG 




ABC 


UA/3088 


ABD 


CRA Letter 2/7/71 


ABH 


U A/ 2486 


ABL 


UA/2613 


ABS 


CRA Letter 20/1/7 


ABW 


SG/6089/09/N-2 


ABX 


CRA Letter 3699 


ACA 


SG/6348/09/N-2 


ACB 


SG/6348/09/N-2 


ACDC 


SG/6348/09/N-2 


ACDE 


SG/6348/09/N-2 


ACF 


SG/651V09/N-2 


AC J 


SG/ 7640/09/2 


ACL 


SG/ 7640/09/2 


ACM 


CRA MSG 270473/7 


ACP 


SG/6422 


ACR 


SG/ 7640/09/2 


ACS 


SG/ 7640/09/2 


ACT 


SG/7641/09/2 


ACV 


SG/7770/09/N-2 


ACW 


SG/7641/09/2 


ACX 


SG/7641/09/2 


AEA 


SG/7640/09/2 


AED 


UA/4212 


AEE 


CRA MSG 310773/1 


AEF 


SG/7770/09/N-2 


AEG 


SG/7641/09/2 


AEH 


SG/7770/09/N-2 


AEK 


SG,'7770/09/N-2 



SAN MARCO SUPPORT, TASK J TO CONTRACT NASl-10000 



TASK 



COST W/ 
8.119% FEE 



H2O2 Equipment Rework 

Logistical Support for SMER 

Miscellaneous Materials for SMER 

Microfilm Equipment for CRA 

A/C Spares and Installation 

Transformer for SMER 

Certification Training 

Miscellaneous Materials for SMER 

Miscellaneous Spares for SMER 

Logistics Support to SMER 

K & E Transits 

Drawing Maintenance 

Update SMOP & Configuration Control 

Range Conlrol Center Spares 

S-178 & Sub GSE Mods 

Genesco Rate Table 

Lima Crane Inspection 

Refurbishment of SMER Equipment 

Certification Materials 

Miscellaneous Spares for SMER 

Lima Crane Spares 

Miscellaneous Materials for SMER 

LTV Technical Support to SMER 

LTV Technical Support to Rome 

Battery Simulators 

Air Conditioning & ITEK Spares 

Batteries & Spares for SM C-2 

Hydrogen Peroxide for SMER 

LTV Technical Support to SMER 

Logistics Support to SMER 

Miscellaneous Materials for SMER 



$ 



8.132 
22,067 
31 ,282 
12,275 
10,188 
198 
10,771 
26,759 
1,777 
35,968 
12,118 
4,600 
15.113 
213 
198,762 
13,356 
4,590 
13,037 
544 

5,957 
6,615 
3.214 
7.086 

17,658 

532 

5.292 

31.283 
2,429 

11,722 

11,839 
8.943 



TOTAL 



$534,350 



387 



TABLE CXVIII - SAN MARCO SUPPORT, CONTRACT NAS1-12500 TASK J 



TASK NO. 


CRA AUTHORITY 


J-3 


SG/6348/09/N-2 


J-k 


S(/7975/09/N-2 


J-6-1 


SG/7977/09/N-2 


J-6-2 


SGA385, 121173A 


J-6-3 


SG/7770/09/N-2 


J-6-h 


SG/777O/09/N-2 


J-6-5 


SG/7770/09/N-2 


J-6-6 


SG/7770/09/N-2 


J-6-7 


SG/7770/09/N-2 


J-6-8 


UIK/k38S 


J-6-9 


271273/1 


J-6-10 


291373/1 


J-6-n 


271173/2 


J-6-12 


08/1200Z 


J-6-1 3 


121720Z, OinCtZ 


J-6-li» 


D1037'»/l 


J-6-1 5 


UA/'»553, l'»0921/74 


J-6-16 


UA/ifSg^f, ^638, '»639 


J-6-17 


SG/8805/09/'» 


J-6-18 


2067'»/2 


J-6-19 


SG/850't/09/^ 


J-6-20 


UA/ffSS** 


J-6-21 


UA/ii6i»0 


J-6-22 


UA/4673 


J-6-23 


DA/kykk 


J-6-2i» 


Ul\/k7k5 


J-6-25 


UA/i»7i»8 


J-6-26 


02097'»/1, 16077V1 


J-6-27 


23/1 220Z 


J-6-28 


UA/h7'»^ 


J-6-29 


SG/8805/09/'* 


J-6-30 


CRA letter #2 12/16/7*1 


J-6-31 


CRA letter 11/21/75 


J-6-32 


CRA letter 12/17/7A 


J-6-33 


SG/8805/09/N-^ 


J-6-3^ 


CRA Telex 2/4/75 


J-6-35 


CRA Telex 3/7/75 


J-6-36 


CRA Telex 3/10/75 


J-6-37 


UA '*957, 07/1225 05/1088 


J-6-38 


CRA Telex 3/10/75 


J-6-39 


CRA Telex 7/21/75 


J-6-^0 


CRA letter 11/21/7'* 


J-6-ifl 


UA 5087 


J-6-i.2 


UA 5087 


J-6-'43 


UA 5052 


J-e-kh 


UA 5051 


J-6-/J5 


UA 5086 


J-6-i»6 


UA 5087 


J-6-'t7 


UA 5085 


J-6-^ 


CRA Telex 3-2*1-76 




CRA Telex 3-25-76 


J-6-50 


CRA Telex 3-2it-76 


J-6-51 


CRA Telex *f-1-76 


J-6-53 


UA 5030 6-26-75 


J-7 


SG/7770/09/N2 


J-8 


SG/6it22 


J-11 


SG/8306 


J-12 


SG/8805/09/4 


J-1if 


OIO77VI 


J-16 


UA 508it 



TASK 

Configuration Management 
Logistics Support to San Marco Range 
Air Conditioning Equipment for Telemetry Room 
Headsets, Filters, Ring, Alinement Tools 
Miscellaneous Tools and Capacitors 
Connectors, Valves, Squibs 
TEKTRONIC Probe and Tracer Spares 
Stop Assembly and Direction Plate 
MIT Station Spares, Generator Spares 
Electrical Spares 
Converter and Generator Spares 

Telemetry Room Spares and Miscellaneous Materials 
Miscellaneous Materials and MIT Station Spares 
Communication Spares 
Miscellaneous Materials 
S-193 and Sub. Mod. Kits 
Crane Motor and Miscellaneous Spares 
Miscellaneous Materials 
Electrical Components 
Hewlett Packard Components 
Interferometer System 
Miscellaneous Materials 
Roller Bearings and Potentiometers 
Transformer 
Motor Boat Spares 
Submarine Pumps 
Beckman Testers 
Electrical Spares 
Ingersoll Rand and Forklift Spares 
Marine Engine Type 76O 

Technical Support for S-193 Modifications 
Drafting Support S-193 Modifications 
Misc. LeTourneau and S. Atlanta Spares 
DAF Engine and Spares 
Logistic Support for S-19'» Processing 
Electrical Technical Support for S-193 Mods. 
Mechanical Technical Support S-19'» Processing 
Mechanical Foreman S-19'> Processing 
Electronic Spares, Lost Materials 
Hydrogen Peroxide 

Mechanical Foreman to SMER (Oct-Nov 1975) 
Electrical Test Equipment £ LeTourneau Spares 
Volume I I of SMOP 

Preservation of Motor Shipping Vans 
Telemetry Station Spares 
Electronic Spares 

Electronic Test Set, DAF, & A/C Spares 
Structures Engineer to SMER 
Materials for S3t Cable Plant 
Update Long Range Spares Report 

Personnel Profficiency Program Support 

Mechanical Technician Support to SMER 

Certification Materials 

Shipping Charges for Mission Procurements 

Refurbishment of San Marco Range Equipment 

Operations Consultant for S-I87 

Logistics Support through S-187 

interim Logistics Support 

Sodium Payload Procurement from GCA 



CRA 
TOTAL COST 

$ 8T,6*f9 
25,798 

10,684 
7,611 
1.766 
2,768 
2,506 
1,774 

25,364 
1,246 
8,969 
4,947 

38,726 

10,259 

2,529 

44,527 

5.856 

30,011 

46,142 

1,630 

51 ,340 

247 

159 

249 

2,636 

8.997 

2,088 

15,736 

2,893 

14,156 

18,161 

10,993 

19,666 

35.305 

19,192 

28,153 

8,652 

8,014 

19,828 

3,168 

6,459 

41 ,476 

66,406 

16,215 

6,367 

16,041 

54.358 

2,748 

3.890 

9,560 

12 596 

23!892 

7,714 

2,580 

58,049 

26,486 

15,247 

22,459 

11,862 

51 ,260 



TOTAL 



$1,080,056 



388 



lASA 



TABLE CXIX - (EXHIBIT) 



Roo'v to Ann 



National Aeronautics and 
Space Administration 

Washington, DC 
20546 



oi MLE-9 



15 JUN 1978 



Professor Luigi Broglio 

Director, Centro Ricerche Aerospaziali 

Universita Degli Studi di Roma 

Via Salaria N. 851 

Rome, Italy 00199 



Dear Professor Broglio : 

The current status of the San Marco C Trust Fund is reported 
below. 

1. Funds Received 

The following deposits of funds were received directly 
from the University of Rome: 



February 1969 


$ 


48,009.06 


May 1970 


$ 


250,000.00 


October 1972 


$ 


500,000.00 


May 1973 


$ 


762,647.24 


December 1974 


i_ 


453,600.00 



Total 



$2,014,256.30 



Also, the following payments for services provided by the 
CRA under NJ\SA Contracts NASW-1761 and NASW-2135 were 
deposited to the San Marco account: 



SAS-C Support - June 1975 
UK-5 Support - January 1977 
UK-5 Support - January 1977 
MITS Support - June 1977 
MITS Support - October 1977 

Total 



$200,000.00 
$ 73,431.00 
$ 8,032.00 
$101,900.00 
$ 35,077.00 

$418,440.00 



389 

TABLE CXIX Continued - (EXHIBIT) 

The total funding deposited to the San Marco account is 
, $2,432,696.30. 

2. Funds Obligated 

As of May 31, 1978, the following obligations have 
been made for the CRA: 



Item 



Amount 



Mnf'^'c^ • . ^ 30,313.03 

Motor Shxppmg Containers 5 23 616 81 

Dummy Motor Shipment ^ 2*145*82 

Range Expendables and Shipping Charges $ 114 '411*13 

LTV invoices ^ 78,' 272.* 00 

MPS-19 Spare Parts ^ 8 232 19 

Return of Motor Containers § 13*717*48 

Spare Parts ^ 179,' 666^02 

H2O2 System Rework ^ 34,415.09 

Clean Room Equipment ' ^ ^4 085 64 

S-173C/S.M.-C Vehicle Shipment $ 58* 240^44 

Nike Apache Rockets g 4l' 777*21 

Support of Nike-Apache Launch Ops. $ 7 ! 141 ! 00 

Motor Container Rework/Refurbishment $ 34 ,'059' 00 

Algol III Modifications $ 20,' 000 ! 00 

Microfilm System c 12 209 00 

^^^^^^^ • $ ii;ooo.*oo 

Drawing Maintenance and Logistic Survey, 

S&CC Implementation ^ 49,381 00 

LTV Support to CRA, Rome (1973) $ 17^536! 00 

S&CC Maintenance (NAS 1-10,000) $ 30,'829!oo 

S&CC Maintenance (NAS 1-12,500) $ 25^ 228^00 

Certification Training e 11*557*00 

S-Band Telemetry ^ 251,' 726^13 

Santa Rita Inspection $ 13,310.00 

San Marco C-2 Support/Spare Parts $ 31,272.15 

GSE & Range Equipment Refurbishment $ 29 i 869^00 

Scout Phase V GSE Mod Kits $ 78,974.00 

Scout Phase VI GSE & Telemetry Mod Kits $ 42 ! 030 ! 00 

42" Heat Shield Modifications $ 38,131.00 

Phase VI Mod Kits Installation $ 23!408!oo 



390 



TABLE CXIX Continued - (EXHIBIT) 



Item 

payload Umbilical Arm Rework 

scout S-190C/S.M.-C2 Vehicle Shipment 

Lima Crane Refurbishment 

LTV Logistics Support for S-190C 

Electrical Equipment for t/M Room 

MITS Spare Parts 

communication System Spare Parts 

Scout S-193 and Sub Mod Kits and 

installation 
Radar System Modifications and Maintenance 
San Marco C2 Communication Support 
Sounding Rocket procurement (1974) 
LTV Logistic Support for S-194C 
LTV support for S-187C Processing 
Submarine Cables & Electrical Components 
interferometer System 
LTV Configuration Management Support 
Marine Engine Type 760 
DAF Engine and Spare Parts 
LTV Support at SMER 
LTV Logistic Support 
Standard procedures (SMOP Vol II) 
Spares Program Support (TWX dtd. 

March 24, 1976) 
Logistic support (SG/8805/09/04) 
Configuration Management (SG/6348/09/N-2) 
Operations Support/S-187 (SG/8506) 
Logistic Support/S-187 (SG/8805/09/4) 
Spares System Management (TWX dated 

March 24, 1976) 
Spare Parts (UA/4640) 
S-193 Mods installation (TWX dated 

February 4, 1975) 
personnel proficiency Program (TWX dated 

March 23. 1976) 
Mechanical Tech. Support/SMER (TWX dated 

April 1, 1976) 
Logistic Support/SMER (TWX dated Mar. 24, 

1976) 
Vought Corp. Invoices (SG/10182) 





Amount 


$ 


14,153.00 


$ 


60,969.26 


$ 


18,158.00 


$ 


23,306.00 


$ 


10,684.00 


$ 


48,901.00 


$ 


10,259.00 


$ 


101,941.01 


$ 


17,130.22 


$ 


76,969.00 


$ 


52,508.80 


$ 


19,381.00 


$ 


34,937.00 


$ 


46,094.00 


$ 


51,340.00 


$ 


50,000.00 


$ 


14,156.00 


$ 


30,490.00 


$ 


24,845.00 


$ 


14,900.00 


$ 


73,648.00 


$ 


7,192.00 


$ 


19,192.00 


$ 


795.47 


$ 


1,810.00 


$ 


959.00 


$ 


577.69 


$ 


159.00 


$ 


28,123.00 


$ 


23,892.00 


$ 


7,714.00 


$ 


1,333.84 


? 


51,537.00 



391 



TABLE CXIX Concluded - (EXHIBIT) 

Item 

Vought Corp. Invoices (TWX dated 

August 3, 1976) 
DAF and Electrical Spares (UA 5086) 
GCA Payloads (TWX UA 5084) 

Logistic Support (TWX dated Mar. 23, 1976) 
Certification Program Materials (UA 5030) 



Amount 



$ 74,271.00 

$ 54,354.00 

$ 51,260.00 

$ 11,262.16 

$ 2,580.00 



3. 



Total Obligations $2,551,773.95 

San Marco C Trust Fund Account Balance 



Total Obligations 
Total SMTFA Funding 



$2,551,773.95 
$2,432,696.30 













$ 


119. 


,077, 


,65 


Payments From 
Account : 
SMDDA-8 
SMDDA-9 


San 


Marco 


D 


Deposit 


$ 
? 


84, 

34, 


,884. 
,193, 


.65 
.00 



$ 119,077.65 



San Marco C Trust Fund Balance 



-0- 



Sincerely, 

p. E. Gooai* 

Paul E. Goozh 

Scout^San Marco Program Manager 

Expendable Launch Vehicle Programs 



392 





TABLE CXX 


I2a±£ 




November 


1977 


January 


1978 


May 


1978 


July 


1978 


November 


1978 


March 


1981 


April 


1981 


May 


1981 



- SAN MARCO- D DEPOSIT ACCOUNT 



CWW/ 1-26-82 
Rev. A 

Funds Rec'd 



1. 


GSFC 


2. 




3. 




4. 




5. 


GSFC 


6. 


J2-01 


7. 


J2-02 


8. 


J2-03 


9. 


J2-04 


10. 


J2-05 


11. 


J2-06 


12. 


J2-07 


13. 


J2-08 


14. 


J2-09 


15. 


J2-10 


16. 


J2-11 


17. 


J2-12 


18. 


J2-13 


19. 


J2-14 


20. 


J2-15 


21. 


GSFC 


22. 


J2-16 


23. 


J2-17 


24. 


J2-17A 


25. 


J2-18 


26. 




27. 


GSFC 


28. 


J2-19 


29. 


J2-20 


30. 


J 2-21 


31. 


GSFC 



Item 

Rad I ometer 

Vought Invoices 

Vought Invoices 

Radar Modifications 

Unpaid Commitments from Trust Fund 

Radiometer 

Configuration Management 

Proficiency Training 

Van Storage 

Pay load Storage 

DeLong Inspection 

Generators 

Algol III Feas. Study, SM Scout 

Delong Engineering 

SM Launcher Improvement, SM Scout 

NEMAR Training 

Material - Certification 

Material - Air Compressor 

Motor Generator Shipment 

Support to Launcher Improvement 

Engine Parts 

Tech. Monitoring & Support 

Van Storage 

Storage of Lithium P/L»s & Motor 

Shipping Vans 
Pay load Storage 
Prelim. SM Documentation 
Test Rocket SM Meteorological 
Emergency Procurement 
Phase VII Mod. Kits & Material 
Long-lead Items, Mech. 4 Fluids 
Refurb. SM Components at Vought 
San Marco D Procurement 







$ 300,000.00 






200,000.00 






200,000.00 






200,000.00 






100,000.00 






223,578.00 






126,039.00 






318,609.45 




Total 


$1,783,226.45 


Funds Obi Igatlon 








CRA 


Amt. Authorized/ 


Status 


Auth. 


Disbursed 



Update 

Prog 



SMDDA-1 $ 110,000.00 

SMDDA-5 60,068.00 

SMDDA-9 34,193.00 

SMDDA-1 2 3,500.00 

SMDDA-8 84,456.00 

SMDDA-1 8 100,000.00 

Closed SMDDA-7 19,125,36 

Closed SG 10351/07-3 20,853.95 

Closed SMDDA-6 5,592.86 

Closed SMDDA-6 2,013.99 

Closed SMDDA-8 4,481.55 

Closed SMDDA-1 1 54,708.36 

Closed SMDDA-1 44,678.27 

Closed SMDDA-1 3 31,458.09 

Closed SMDDA-1 4 13,074.78 

Closed SMDDA-1 5 14,487.80 

Closed SMDDA-1 6 5,868.57 

Closed SMDDA-1 7 3,968.74 

Closed SMDDA-1 9 3,474.40 

Closed SMDDA-21 20,271.29 

Closed SMDDA-22 4,935.89 

Closed SMDDA-25 35,600.00 

Closed SMDDA-26 3,346.47 

Open SMDDA-36 4,000.00 

Open SMDDA-27 3,084.00 

Closed SMDDA-24 9,530.95 

UA/6935 4,050.00 

Open SMDDA-28 35,000.00 

Closed SMDDA-29 4,796.65 

Closed SMDDA-30 34,576.30* 

Closed SMDDA-31 15,627.27 

Closed SMDDA-32 35,000.00 



393 



TABLE CXX Concluded - SAN MARCO-D DEPOSIT ACCOUNT 



32 


GSFC 


33. 




34. 




35. 




36. 


GSFC 


37. 


GSFC 


38. 




39. 


J2-22 


40. 




41. 


J2-01 



42. 

43. J2-03 
44. 



Item 

San Marco D Procurement 
Spacecraft Parts Requests 
DFrect to GSFC 

Inspection of CRA Rocket Motors 
San Marco D Proc. & Travel 
San Marco D Procurement 
Spacecraft Umb 1 1 leal Connectors 
Proc. of Misc. Items for Vol. II 
Parts Listing & Elect. Manual 
Vought Quotes 1L-26, -27, -28, 

-29 & -30 
Shipment of MPS-19 Radar & MPS-21 

Spares, Personnel Travel 
Shipment of Misc. Mat' Is to SMER 
Phase VII Mat' Is Procurement 





CRA 


Amt 


. Authorized/ 


Status 


Auth. 
SMDDA-33 




Disbursed 


Closed 


$ 


35,000.00 


Closed 


SMDDA-34 




** 


Closed 


SMDDA-35 




«« 


Closed 


SMDDA-37 




6,206.00 


Closed 


SMDDA-38 




55,000.00 


Closed 


TELEX 3/81 




500,000.00 


Open 


SMDDA-39 




620.00** 


Open 


SMDDA-40 




745.00 


Open 


SMDDA-41 




125.00 


Open 


SMDDA-42 




200,000.00 


Open 


SMDDA-43 




20,600.00 


Open 


SMDDA-44 




5,000.00 


Open 


SMDDA-45 

Total 




130,000.00 




$1 


,779,218.54 




Balance 


$ 


4,007.91 



The two main Phase Vi DOD Scout programs were DOD MIPR's 66-95 and 68-71. 
MIPR 66-95 consisted of six Scout launches: one Phase IV - S-157; three 
Phase V - S-162, S-170 , and 5-1/6; and two Phase VI - S-1 78 and S-182. It 
covered costs from 1967 through 197^. MIPR 68-71 had two Phase VI launches, 
S-179 and S-192. The remainder were Phase VII. MIPR 68-71 covered costs from 
1975 through I985. Table 

Table CXX I lists the total projected DOD program for Phases II through VIII 
for funds through 1979. Tables CXX I I through CXXVII detail MIPR's 66-95 and 
68-71 financial programs. Table CXXVII I itemizes the special DOD P76 program. 
Tables CXXIX through XCCCVI detail the hardware for E-Sections, heat shields, 
on-base costs, production support, spares, range operations, and field services 
as typical program requirements. 



*J2-20.- Proc. of long- lead-time Items. Time from cost quote submitted to CRA and 
approval by CRA requires quicker response; quotes are often for 30 days only, and 
approval Is received after cost quote Is invalid. 
**Funds not Issued from Deposit Account. 
***Purchased under NASI -12500, Task M-4-32, transferred 8 connector to SM DL Program. 







39't 






TABLE 


CXXI - DOD EXPENDITURES 


SCOUT 


( )** 




PHASE VI 1 & 


PHASES 1 1 THROUGH V 


PHASE VI 


SUBSEQUENT 


ss-ii-s-e 








NA492 








1961 


$ 1,800,000 






1S62 


7,900,000 






1965 


3. 3^*8 






62-6 








1962 


$ 7,172,858 






1963 


88't,096 






196'. 


260,281 






1965 


1,26it.759 






1966 


6'(1,'427 






1967 


520,612 






1969 


267,502 






1975 








62-12 








62-13 








62- lit 








63-27 








A63-29 








1962 


975,670 






1963 


3,465,000 






196;. 


'♦6'(,000 






1965 


1,255,299 






1966 


1,086,381 






1969 


217,031 






63-30 








63-32(1962-3) 


l.g** '1,298 






(>l-'*h 








6'.-30 








65-'.2(1965-6) 


iiOO.OOO 






66-87 








A66-95 








1967 


7,198,831 


3.570,855 


'+50,581 


1968 


330,625 


1 ,0t5,529 


2,153,771 


1970 





970 ,883 


50,0'*8 


1971 


263,679 


617.677 


732,000 


1972 




12,327 


20,181 


1973 




1't,7't6 


'i9 ,'t05 


197't 




'1,000 




*68-71 








1968 




1,0'+9,35'* 


2.858.063 


1972 




6,855 


562,666 


197't 




775,0'i7 


10,871,206 


1975 




'16, 36/4 


1.153,636 


1976 




2.556,398 


2.693,529 


197T 






11 ,535 


1977 




'17 


2,270,852 


1978 







't.178,250 


1979 







2,065.'t50 


RST-535(NAVY) 








TOTAL 






90.000 


$38,315,697 


$10,670,082 
ce. Does not 


$30,211,173 


*Navy Program funded by Air For 


include funds 


**Final Costs 









0R8Gi?^AL FAGS "^-^ 
OF POOR QUALiW 



NONSCOUT 


TOTAL 


$6,718,936 


$ 6.718.936 




9.703,3't8 




(1,800,000) 




(7.900.000) 




',3,3't8) 




11,212.996 


89,52'i 


(7,262.382) 


9,190 


(893,286) 




(260,281) 


10.7'i7 


(1,275,506) 


2,000 


(6'.3,'i27) 




(520.612) 




(267,502) 


90,000 


(90,000) 


26'i,395 


26'(,395 


'182,79'* 


't82.79'i 


l,32'i,3'i7 


1.32'i.3'i7 


100,000 


100.000 




7. '163. 381 




(975,670) 




(3, '165, 000) 




('i6'(,000) 




(1,255,299) 




(1,086.381) 




(217,031) 


5,301 


5,301 




1,9'i '1,298 


132,110 


132,110 


223,080 


223,080 




'100,000 


2'i8,000 


2'i8,000 




17, '185 ,138 




(11,220.267) 




(3,529,925) 




(1,020.931) 




(1.613.356) 




(32.508) 




(6'i.15l) 




Ci.ooo) 




31,189,252 




(3,907.'t17) 




(569.521) 




(I1.6'i6,253) 




(1,200,000) 




(5.2'i9.927) 




(11.535) 




(2,270,899) 




Ci. 178. 250) 




(2, 065, '♦50) 




90,000 




(90,000) 


$9,700,'l2'i 


$88,897,376 



395 



TABLE CXXII - DOD COST SUMMARY, 

1. FINAL ESTIMATED COSTS M I PR 66-95 THRU FY74 $17,485,136 

(a) Includes 5 Vehicles $6,103,049 

(b) Includes Annual Costs FY6 7- FY 74 9,561,953 

(c) Per-Launch Costs (5 Vehicles) 986'622 

(d) Special Requirements Thru FY74 1,354^443 

(e) NASA's Share (-520,931) 

2. ESTIMATED COSTS MIPR 68-7I THRU FY86 $120,821,606 

(a) Includes 12 Transit Vehicles, $52,983,258 

Air Force P76-5, & 5 A.F. ITV Veh. 

(b) Includes Annual Costs FY74-FY85 55,^06,956 

(est.) 

(c) Per-Launch Costs (12 Vehicles) 12,431,392 



TABLE CXXII I - SCOUT 66-95 PROGRAM, PER-LAUNCH COST. 

157c 162c I7OCR 176c 182c 178c 



Pref 1 ight Planning 

Data Analys is 

Launch Crew (TDY) 

Travel 

Specials (Estimate) 



1 1 n-cpi i_ i ves 



$ 5,261 


$ 6,592 


16,952 


16,952 


82,143 


82,143 








3,000 


3,000 


:h Physics 











$ 4,363 


$ 10,591 


$ 7,075 


5,736 


32,292 


37,675 


54,174 


41,959 


32,591 





25,000 


25,000 


3,000 


3,000 
97.206 


3,000 
20,412 


106.000 


10 5,286 


10 5,286 



TOTAL $107,356 $108,687 $1,722 $173,273 $315,334 $231,039 



3% 



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399 



ORIGIMAL PAGE 13 
OF POOR QUALITY 



TABLE CXXVII - DOO/SCOUT 68-71 SUMMARY THROUGH 1979^^^ 



Deslg- Vehicle FY 

Vehicles nation Number Phase Launched 



1 
2 
3 
k 
5 
6 



(2) 



(3) 



5) 



m 



N-17 

AF-P76-5 

N-18 

N-19 

N-20 

N-21 



195 
179 
197 
200 
20'f 
192 



VII 

VI 

Vil 

VII 

VII 

VI 



1976 
1976 
197T 
1978 
1979 
1979 



Hardware 

$1,728,933 
1,386,896 
1,781,023 
2,131.281 
2,286,723 
1,825,830 



Cost Per 
Launch 

$ 589,472 

845.682 

575.338 

1.214,301 

1,206,000 

1.257,450 

TOTAL 



(q) DOD A.F. Program P76 (Table CXXVIII) 
(r; DOD-VAFB Reimbursable Servlcei (Table CXXIX) 
(s) DOO-VAFB Utility Coiti (Table CXXX) 
Hard»ara (01) 

(a) Scout E-Sectloni (Table CXXXI 

(b) Scout Heat Shleldi (Table CXXXI I) 

(c) Taik M (01) Loglitlei Coat (Table CXXXI 1 1) 

(d) Taik T (01) Production Support (NAS1-1 5000) (Table CXXX 
Proration of Launch Site Coiti 
(a) Contract NASI -12500 Task N (Table CXXXV) 

Summary of Task N (Table CXXXV I) 

Range Operation and Maintenance Expend I tures-VAFB (Tab 

Range Operation and Maintenance MSO Expend I tu res- VAFB 
. . QSE ixpenditures (Table CXXXIX) 
DOD Audit Servleei (DCASO) (Table CXL) 
Icout Shipping Expenditures (Table CXL I) 
Scout Engineering 
(a) Improvementi Phase VI (Table CXLII) 

R&D Funds-SRT (180 Program) (Table CXLI 

Task R Beta lis 



it! 

(d) 
Proi 

(e) 

(d) 

(a) 



IV) 



Total 

$2,318,405 
2.232,578 
2.356,361 
3.345.682 
3.492,723 
3.083.280 

$16,829,029 

Page 
To5 

401 

402 

403 
406 
408 
410 



(e) 



II) 



-1- Contract NASI-IOeOO 
-2- Contract NAS1-12S00 
■3- Contract NAS1-1f10O 



(d) Ta§k § Details 

-1- Contract NASI -10900 
-2- Centragt NASI -12100 

(@) R&D Support 



(Table LVI) 
(Table LVI I 
(Table XLIX 



(Table LVI 1 1) 
(Table LIX) 



■1- Contract NAi1-10itil (Table CXLIV) 
-2- Conlraet NASI -10^2 (Table CXLV) 
-I- Contract NAi1-10itS3 (Table CXLV I) 
■4- Contract NAil-1 0^*14 (Table CXLVII) 
-i" contraet NAii-ISiOO (Table gXLVlii) 
(i) Contract NAI1-12i00, -11000, -1|100 

-a- itandard Ta§k § (Table CXL IX) 

=b- MIsilen Pecyllari (Table CL) 

=§» lp§6iali (Table CLI) 

=d= ihilf Life (Table CLII) 
§§§ui Travel impend! lures (Appendix L) 

(a) Travel i§llffl8tg§ (f@F ludfet) for Typleal Year 1|7| 

(b) Travel A§lual§ for FY 1171 

l§) Travel Ailu§l§ for FY 1171 Threufh FY 1171 



411 
413 

le CXXXV 1 1) 

(Table CXXXV III) 
420 
421 
422 

424 
425 

238 

240 
182 

243 
24s 

42S 
427 

428 
429 
430 

431 
432 
433 
433 



414 
417 



WtmT 



leefl addiiienal launghei planned after 1|7I for the Navy. 



^°° OF POOR QUALITY 

TABLE CXXVIII " COST ESTIMATES FOR P76-5 (S-179) 

1. Vehicle Procurement $1,421,221 

Vehicle Hardware $530,^65 

Motors 362,934 

Certification and Processing 3^1,732 

Vehicle Processing $1^8,375 

34- inch Heat Shield Mods (HEK) 31,675 

Fit Check Buildup (JDD) R-I65 16,269 

Personnel from Dallas (HGG) 87,794 

Retest Vehicle Components (3) 57i6l9 

Tooling 68,502 

Spares 50,529 

Mission Peculiars 67,059 

Fourth-Stage Telemetry (JB) R-I63 41,9^7 

Vehicle Reassignment (JO) R-I65 12,711 

Guidance Reprograming (JDE) R-I65 5,721 

Roll Yaw (7199 M14) 6,680 

2. Transportation 27,034 

3. Field Crew 220,364 

4. Project Management and Engineering Support 236,562 

Systems Engineering 48,310 

Pref light Planning (RI65) 20,599 

Mission Integration 25,153 

Heat Shield Design (BKH) 2,608 

Interface Dwg .-Brochure (JDA) R-I65 8,410 

New Trajectory (Prel iminary) (BEF) 3,797 

Environmental Study (BGD) 10,338 

Data Reduction (RI65) 42,500 

LTV Incentive Award 100,000 

5. DOD Contract Administration 

6. Travel 

7. •.VRange Services - L29075A 

TOTAL 



(a) R92-NAS1-10000 - $9,258.00. 
R164-NAS1 -12500 - $7,411.00. 
RI73-NASI -12500 - $28,736.00. 
R9I-NASI-I25OO - $12,214.00. 





15,080 




24,396 




62,429 


$2 


,007,086 



ifOI 



ORIGINAL PAGE [3 
OF POOR QUALiTY 



$127, 8V+ 



MIPR 

VAFB ASSESSMENT (RECURR ING) fa) 

L-88316 (SAMTEC)- QUINTRON 
L-5098A (SAMTEC)- QUINTRON 
L-22387A (SAMTEC)- QUINTRON 
L-52306A (SAMTEC)- QUINTRON 
L-egiitSA (SAMTEC)- QUINTRON 
L-8652IA (SAWTEC)- QUINTRON 

VAFB UTILITIES 

L-50725A 
L-68209A 
L-86494A 
VAFB ASSESSMENT (NONRECURRING) 

L-29062A (SAMSO)(C)(Stearns Roger) 210,000 
L-93196 (SAMSO) 100,000 

VAFB RANGE SUPPORT 

L-793OA NAVY (Standby 192) 
L-793OA AEROS (WS) 
L-793OA ANS-A 
L-29075A TRANSIT 

TIP- 1 1 

TIP-lll 

AF-(179) 

AF-(179)Aircraft 
L-24697A ESRO-IV 
L-2738IA DAD 
L-50692A TIP-lll 
U-5O696A NAVY Standby (BPDAO) 
L-5O696A NAVY TRANSAT 
1-461 6A UK-X4 

L-682OOA NOVA (BPDAO) 

L-68202A HCMM 

1-66493 A MAGSAT (E0D49) 



TABLE CXXIX - VAFB RtlMBdRSABLE SERVICES 
FY 1974 FY 1975 FY 1976 FY 197T 



FY 1977 FY 1978 FY 1979 FY 1980 



$147,154 



2,694 

640,350 

49,238 



$ 75,000 $23,698 



67,250 266.938 



40 
44,100 
44,000 
29.059 
19.585 
779.465 
117.500 



829.897 



$ 70.526 



3,243 



26,055 



31,800 



7,315 

7.315 

40,985 



$ 77,500 $ 42,393 



12,000 



100,000 100,000 



2,114 



56,897 



153,200 
89,248 



19,000 



$ 9'»,922 

25,000 
50,000 



305 
165,300 



' WAFB ASSESSMENT VIA KSC 

OA-76-490 (23-4-27 (O-LCOO-295)) 

VAFB Range SPO SUPPORT 

L-682OIA (E0D40) 
L-86492A (E0D40) 

HAWTHORNE STORAGE 

L-68203A-3 
L-682O8A-3 

MSO-GSA CAR (03) 

SUBAUTHORIZATION TO KSC 
MSO-SUPPORT BY KSC (04) 

SUBAUTHORIZATION TO KSC 

MSO-OPEN PURCHASE REQUESTS 
LaRC Contract (6308.OOOI) 



15,000 



22,011 



31.995 



75,000 



42,989 
4,500 



37,100 



60,000 
1,944 



1 .500 



40,000 



100,000 



MS 0- VAFB 



NASI-I5077 



100,000 



•'- From Subauthor ization. 
(Q)507„ DOD, 50% NASA. 
(C) Includes $83,202 C of F. 



402 



OF POOR QUALS'FY 









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403 



ORIGSnAL PAQE IS 
OF POOR QL'ALITY 



TABLE CXXXl(a) - SCOUT E-SECTIONS 



NO.' 


CONTRACT 
3899 


SPACECRAFT ASSIGNED 


*o; 


Test (SM-C - Training) 


*1P 


1928 


SECOR/SEV 


*1, 


3899 


CAS-A 


*2P 


1928 


SOLRAD-A 


2 


3899 


OFO (E-Section Tests) 


3 


3899 


ESRO IIA 


*U' 


3899 


UK-E 


5- 


3899 


UK-E 


6 


3899 


SSS-A 


*7 


3899 


AF-0V3-1 


*8 


3899 


AF-OV3-4 


A9 


3899 


AF-OV3-3 


*10 


3899 


AF-OV3-2 


*11 


3899 


AF-OV3-5 


*12 


3899 


ESRO I (Failed) 


13 


3899 


OVJL 


14 


3899 


ADIE-C 


15 


3899 


ESRO I 


*16 


5592-1 


ADIE-C 


*17 


5592-1 


SOLRAD-B 


*18 


5592-1 


ESRO IIA 


*19 


5592-1 


ESRO lA 


*20 


5592-1 


AF-OV3-6 


*21 


5592-1 


GRS-Al 


*22 


5592-1 


ESRO IIB 


**23 


ERNO 15468 


German-Direct (ERNO) 


24 


6935 


GRS-A 


25 


6935 


CAS-A 


26 


6935 


R>fS 


27 


6935 


UK-4 


*28 


6935 


UK-6 (Failed) 


*29 


6935 


PAET 


30 


6935 


Returned to LRC PAET 


31 


6935 


UK-4 


32 


6935 


ESRO-IV 


33 


6935 


GRS-B 


*34 


6935 


FSRO-IB 


*35 


6935 


OFO /RMS 


*36 


6935 


CAS-A 


*37 


6935 


SOLRAD-C 


**38-41 


BM34616 


German-Direct (Junkers) 


42 


7256 


UK-6 (Modified) 


**A43 


7256 


UK-6 (Partially modified) 


44 


/256 


ESRO-IV 


*45 


7256 


ESRO-IV 


*46 


7256 


AEROS-A 


47 


7256 


UK-X4 



VEHICLE ASSIGNED 

Test 

S-131 

Test 

S-138 

Test 

Test 

S-155 

Test 

Test 

S-145 

S-147 

S-148 

S-150 

S-151 

Test 

Test 

Test 

Test 

S-165 

S-160 

S-152 

S-167 

S-158 

S-169 

S-161 

Test 

Test 

Test 

Test 

Test 

Test 

S-144 

Test 

S-183 

Test 

Test 

S-172 

S-174 

S-180 

S-177 

Not NASA 

Government Stores 

Government Stores 

Test at ESRO 

S-185 

S-181 

Test in England 



*Expended. **Direct Procurement by Germany, not NASA. 
***Assigned to UK-5 (not used) . 



^f^l ■">"3" 



404 



OF POOR QUALiVV 



NO. 



TABLE CXXXl(a) Concluded - SCOUT E-SECTIONS 

CONTRACT SPACECRAFT ASSIGNED VEHICLE ASSIGNED 



*48 


7256 




mc-x4 




*49 


7256 




AEROS- 


-B 


50 


7256 




UK-X4 




51 


7256 




UK-6 


CPartially modified) 


52 


7256 




UK- 6 




53 


7256 








54 


7256 








*201 


10000 R4 






Vought 


202 


10000 R4 






ANS 


203 


10000 R4 






UK- 5 


*204 


10000 Mod 


21 


Task T 


LTC-5 


*205 


lOOOO Mod 


21 


Task T 


Vought 


*206 


10000 Mod 


21 


Task T 


ANS 


207 


10000 Mod 


21 


Task T 


UK-6 


208 


1250O-SOO6 






UK-6 


209 


1250O-SO06 








*210 


12500-S006 






Vought 


211 


125OO-SO06 






SM-Dl 


212 


12500-S006 






SM-Dl 
VouEht 


*213 


12500-S006 







S-188 

S-186 

Test in England 

Government Stores 

Government Stores 

Government Stores 

Government Stores 

Tested to Failure 

Test 

Test 

S-187 

Tested-NonfUghtworthy 

S-189 

S-198 

Test 

Government Stores 

Test 

S-206 

Government Stores 

Test 



TABLE CXXXI(b) - SCOUT E-25 SECTIONS 



*251 


10500-4 


Vought 


*252 


10500-4 


GP-A 


253 


10500-4 


DAD 


*254 


10500-4 


DAD 


255 


10500-4 


GP-A 


256 


12500-5006 


HCM^1 


*257 


12500-S006 


HOIM 


258 


12500-S006 


SAGE 


259 


12500-S006 


SAGE 


260 


12500-S006 




261 


12500-S006 





TABLE CXXXI(c) - SCOUT E-G SECTIONS 



1 


6935-36 


SSS-A 


*2 


69350-36 


Vought 


*3 


6935-36 


Vought 


*4 


6935-36 


SSS-A 


5 


6935-36 


S»'-D.4 


6 


6935-36 


SM-D>« 
TABLE CXXXI(d) - SCOUT 


NO. 


CONTRACT 


SPACKCPAFT ASSIGNED 


*1 


6868 


Vought 


2 


6868 


SSS 


3 


6935-37 




4 


6935-37 


Modified to 102 


5 


6935-37 


Modified to 101 


6 


6935-37 


Vought 


7 


6935-37 


Vought 


*101 


10000 


IJAl/KFYE (From IIo. 5) 


'^102 


10000 


UAV/ICFYF (From No. 4) 


*Exper 


ded 





Test Unit 

S-193 

Test Unit 

S-196 

Test Unit 

at Boeing 

S-201 

Test Unit 

S-202 

Government Stores 

Government Stores 



At GSFC 

Tes t-Konf ligh twor thy 

Tes t-Nonf lightworthy 

S-163 

Government Stores 

S-207 



VEHICLE ASSIGNED 

Test 

Test-At GSFC 
Government Stores 
Test 

Government Stores 
Government Stores 
Test-In Gov't. Stores 
S-191 



405 



TABLE CXXXI(e) - SCOUT E- & G-SECTIONS PROCUREMENT 



P.R. NO, 



E-G SECTION 



CONTRACT 



DESCRIPTION 



FUNDS 



AMOUNT 



(6-S$S, 2-Test. 2-Unassigned) 
60.400.954 NASI -6935-36 

G-SECTION 

(7-Hawkeye, 3-Test, 3-Unassiqned) 

60.900.010 NASl-6935-37 

E-SECTIONA 



Scout E-G Separation Sys. 
E-G SECTION SUBTOTAL 



490-PJ(MP) $150.120.00 
$ 150,120.00 



Proc. 5 G-Sections 
G-SECTION SUBTOTAL 



490-PM(MP) $ 28,900.00 
$ 28,900.00 



(13 (GR-1-4-REIMB.) CAS-B. ESRO IV. AEROS-B. UK-X'4, 2-Test. 6 Unassigned. Phase VI) 



60.900.094 
60.900.023 
60.900.010 
60.400.931 
66.000.013 

66.000.171 



NASI -6935-51 

NASl-7256-33-Ca31-S 

NASl-7256-33-Ca31-S 

NASI-IOOOO-R-23 

NASl-10000-9-Ca11-S 



NAS1-10000-24-T 

E-SECTION SUBTOTAL 
200 SERIES E-SECTION. UK-5, ANSA. 4-Te5t. 7-Unassiqned 



E-Section Test Rework, UK-X4 490-PK(MP) $ 8,490.00 

Procurement of 6 E-Sections 490 30.439.00 

Procurement of 7 E-Sections 490 62,901.00 

Deter, of Roll Momen. Inertia 490-PL(MP) 8.I33.OO 

Inter. 4th Stg,S-Band/E-Sect. 490-PK(PI) 3,431.00 

(Item 324. J.O. E6OOOS) 

Fabricate 4 E-Sect. Castings 490 



27,500.00 
$140,894.00 



6600.0449 



NAS1-10000-R4 
NASI- 10000-21 -T 
NASI-I25OO-SOO6 
NAS1-12500-R28 



3 E-Sections, 200 Series, Incl. Dev. 

4 E-Sections, 200 Series 
6 E-Sections, 200 Series 



$135,040.00 
27,500.00 
84,426.00 
E-SectJ Sep. Sys. Clamp 490-PJ(MP) 4,075.00 

200 SERIES E-SECTION SUBTOTAL $251,041.00 






(n-GP-A, HCMM. DAD. 3 Test. 4-Unass igned) 



NASI -10500-4 
NASI-I25OO-SOO6 



Design & Fab. Large Sep. System 
6 E-Sections - 25 Series 

25 SERIES E-SECTION SUBTOTAL 



$225,125.00 
84.426.00 

$309,551.00 



TOTAL 



$300,506.00 



ORlGSr^AL PAQE 13 
OF POOR QUALITY 



406 



P.R. NO. 

P2Y-021 

P2Y-021 

P25-018 

P25-088 

PO635I 

POOSgil 

P39-012 

POI3I5 

POI3I5 

P05695 

PO595O 

20.200.070 

20.200.019 

20.200.123 

PO5678 

20.200.170 

20.200.215 

20.200.22't 

20.200,276 

20.200.286 

20.200.421 

20.200.489 

20.200.561 

20.200.628 

20.200.643 

20.200.678 

20.200.675 

60. 400. 116 

60.400.200 

60.400.210 

60.400.264 

60.400.414 

60.400.514 

20.200.652 

20.200.656 

60.400.011 

20.200.715 

60.400.273 

60.400.272 

60.400.280 

60.400.339 

60.400.360 

60.400.396 

60.400.644 

60.400.667 

60.400.759 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600. 0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

6600.0921 

5500.0921 



ORDER NO. 



NASI 

NASI- 

NASI 

NASI 

NASI 

NASI' 

NASI 

NASI 

NASI 

NASI 

NASI' 

NASI 

NASI 

NASI' 

NASI 

NASI- 

NASI 

NASI 

NAS1- 

NAS1 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 

NASI 



-1295-7(c3) 

-1295-7(c3) 

-1 295-1 5(c24) 

-1295-1 5 (c24) 

-1295-24 

-1 295-25 (c38) 

-1295-25{c38) 

-1295-25(c42) 

-1295-25{c42) 

-1295-25(c47) 

-1295-25{c50) 

-1295-25 

-1295-29(c57) 

-1295-29(c67) 

-1295-32(c50) 

-1295-32(c68) 

-1295-32{c70) 

-1 295-32 {c71) 

-1295-32(c74) 

-1295-32{c75) 

-1295-35 

-1295-35 

-1295-35 

-1295-36 

-3589-2 (c3) 

-3589-5 (c6) 

-3589-5 (c7) 

-3589-1 2(c25) 

-3589-l6(c36) 

-3589-l6(c37) 

-3589-1 6 (c40) 

-3589-20{c47) 

-3589-20(c47) 

-3899-3 

-3899-3 

-3899-5 

-3899-10 

-3899-26 

-3899-30 

-3899-32 

-3899-32 

-3899-39 

-3899-39 

-5592-9 

-5592-9 

-5610-7 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 

-5610 



TABLE CXXXIl(a) - 34- INCH HEAT SHIELD 

ITEM DESCRIPTION 

Heat Shields 

Heat Shields 

Heat Shields, S-1 14,124,129 

Heat Shields, S-1l4,123,129 

2 Heat Shields for San Marco 

Heat Shields 

Heat Shields 

Heat Shield Mods 

Mod's 11 Heat Shields 

S-127 Heat Shield A-7 Eject. Test 

S-66 Heat Shield, A-2 

S-48 Heat Shield, A-9 

S-55C Heat Shield S/N 124 

Heat Shield RFD-2, A-12 

S-52 Heat Shield, A-7 

S-56B Heat Shield, A-13 

Heat Shield 

Modify Heat Shield A-8 

A-8 Heat Shield Ejection Test 

A-14 Heat Shield 

Modify A-12 Heat Shield 

A-10 Heat Shield for S-55C Mod. 

Modify Heat Shield A-12 

RFD-2 A-12 Heat Shield Test 

Fit Check A-6 Heat Shield 

Mod. to A-2 Heat Shield 

Mod. to A-9 Heat Shield 

Apply Cork Insulation to A-2 Heat Shield 

Apply Cork Insulation to A-23 H/S 

Fab. Heat Shield A-26 for SOLRAD 

Heat Shield A-27 (SECOR) 

Mod. A-14 Heat Shield 

Torque Tube, A-14 

H/S A-21 , Fit and Ejection Test, AD/IB 

H/S A-21, Fit and Ejection Test, RFD2A 

Fit and Ejection Test, A-2/S-66A 

Fit Check, A-23/S-66B 

Heat Shield Ejection Test, A-26 

Apply Cork 22 Heat Shields 

Heat Shield Fit Check, A-27 and SECOR 

Heat Shield A-27 Ejection Test 

Configuration Heat Shield A-28/FR-1 

A-28 Heat Shield 



056 
071 
099 



Heat Sh 



Evaluate Heat Shield for Sunblazer P/L 



Heat Sh 



1 Heat Shield 



Heat Sh 



1 Heat Shield. ESRO IB 



Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 



eld 



eld and D-Section Mods, 



eld. One 



eld A-43, San Marco B 

eld A-44, N-13 

eld A-45, ESRO- I 

eld A-46, SOLRAD 

eld A-47, AD/I-C 

eld A-48, RAM C-B 

eld A-49, ESRO- I IB 

eld A-5O, N-16 

eld A-51 , Navy Inventory 

eld A-52, Navy Inventory 

eld A-53, GRS-A 

eld A-54, San Marco C 

eld A-55, N-14 

eld A-56, ESRO- IB 

eld A-57, OFO 



TOTAL 

101,864.00 
142,037.00 

4,624.00 
16,000.00 
13,373.00 
34,368.00 
125,000.00 
39,813.00 
12,500.00 
10,680.00 
29.688.00 
28,711.00 

8,20<».00 
27,211.00 
19,638.00 
30.947.00 
27,938.00 

4,799.00 

5,890.00 

31.012.00 
1,800.00 

10,242.00 
1,587.00 

16.934.00 
672.00 
4,082.00 
4,255.00 
2,302.00 
1,440,00 
1,817.00 
1.775.00 
7,000.00 
7,871.00 
3,350.00 
7,000.00 

2,500.00 

727.00 

9.150.00 

12.198.00 
7,500.00 
2,413.00 

13.300.00 
5.700.00 
3,430.00 

10,000.00 
6,510.00 
1,100.00 

14,300.00 
1.110.00 

16,500,00 

16,500.00 

16,500.00 
16,500.00 
16,500.00 
16,500.00 
16,500.00 
16,500.00 
16,500.00 
16.500.00 
16,500.00 
16,500.00 
16.500.00 
16.500.00 
16.500.00 



OF POOR QUALITY 



407 



P.R. NO. ORDER NO. 



TABLE CXXXII(a) Concluded - 34- INCH HEAT SHIELD 
ITEM DESCRIPTION 



60.400.718 

6600.0999 

6600.0999 

6600.0999 

6600.0999 

6600.0999 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0932 

6600.0939 

60.400.931 

6600.0931 

60.400.931 

6600.0280 

6600.0341 

6600.0280 

6600.0173 

6600.0449 



NASl-6020-10(c3)-K 

NASI -6935-41 -2 

NASI -6935-41 -2 

NASI -6935-41 -2 

NASI -6935-41 -2 

NASI -6935-41 -2 

NASI -7199 

NASI -7199 

NAS1-7199 

NASI-7199 

NASI-7199 

NASI-7199 

NASI-7199 

NASI-7199 

NASI-7199 

NASI-7199 

NASI-7199 
NASI-7199 
NASI-7199 
NASI-7199 
NASI-7199 
NASI-7199 
NASI-7199 

NASl-7256-33-Ca33-S 
NASI -1 0000-1 7-R39 
NASI -10000-27 
NAS1-10000-R33 
NASI -11 000-10 
NASI -11 000-10 
NASI -11 000-10 
NASI -11000-10 
NASI-I25OO-I8-RII8 



PHASES VI ANDjm 

6600.0999 

60.900.051 

6600.0999 

6600.0999 

6600.0999 

6600.0999 

6600.0999 

66.000.057 

60. 900. 082 

60.900.051 

6600.0999 

6600.0999 

6600,0999 

6600.0999 

6600.0999 

66.000.057 

66.000. 280 

6600.0341 

6600.0280 

6600.0173 



NASI -6935- 
NASI -6935- 
NASI -6935- 
NASI -6935- 
NASl-6935- 
NASI -693 5- 
NASl-6935- 
NASl-6935- 
NASl-6935- 
NASI -6935- 
NAS1-6935- 
NASl-6935- 
NASl-6935- 
NASl-6935- 
NASI -6935- 



•41 

•41 

41-2 

■41-2 

41-2 

41-2 

41-2 

41-4 

41-4 

41-4 

41-7 

41-7 

41-7 

41-7 

41-7 



NASI -6935-41 -9 

MAC 1 _1 t nr\r\ t f\ 

NASI -11 000-10 
NASI -11000-10 
NAS1-11000-10 



Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Heat Sh 
Fab 



eld Mods and Fit Check 

012 Heat Shield A-402, MTS-A 

013 Heat Shield A-404, 

014 Heat Shield A-405, Hawkeye 

015 Heat Shield A-406, ANS-A 
017 Heat Shield A-403, ESRO-IV 

eld A-58, GRP-A 

eld, A-59, SOLRAD-D 

eld, A-60, CAS-A 

eld, A-61, SAS-A 

eld, A-62, RAM-C-C 

eld, A-63, UK-4 

eld, A-64, TIP-II 

eld, A-65, CAS-A 

eld, A-66, San Marco C-2 

eld, A-67, NA-21 

eld, A-68, GP-A 

eld, A-69 

eld. A- 70 

eld, A-71 

eld. A- 72 

eld, A-73 

eld, A-74 
153 Fab. SOU<AD-C Protective P/L Shield(A-59) 

392 Cooling Air Sep. H/S A-406 S- Field Sup. 

621 N-18 H/S Des. and Mod., A-51 

386 Heat Shield Ducting for RTG 

043 2 Heat Shields, A-411/N0VA-I ,A-412/MAGSAT 

044 2 Heat Shields, A-407/TIP-I, A-408/TIP-II 

045 1 Heat Shield, A-409/P76-5 
054 1 Heat Shield, A-410/TRANSAT 

210 Fit Test, Seat Shield A-408/TIP-II 

TOTAL 34- INCH HEAT SHIELD 
TABLE CXXX 11(b) - 42- INCH HEAT SHIELD 



0l6 Design of Heat Shield 

008 Heat Shield, A-501 Test 

Oil Heat Shield, A-502 Test 

018 Heat Shield, A-503, GP-A 

019 Heat Shield, A-504, AEROS-A 

025 Heat Shield, A-505, UK-5 

026 Heat Shield, A-5O6, UK-X4 

027 Heat Shield, A-507, AEROS-B 

028 Heat Shield, A-5O8, SAS-C 

029 Design of Heat Shield 

020 Heat Shield, AEROS-B 

021 Door for Heat Shield, UK-X4 

022 Door for Heat Shield, SAS-C 

023 Door for Heat Shield, UK-5 

024 Door for Heat Shield, AEROS-A 

030 Heat Shield 

043 2 Heai. Snteids, A-505, A-510 

044 2 Heat Shields, A-510, A-512 

045 1 Heat Shield, A-513 
054 1 Heat Shield, A-514 

PHASES VI AND VII SUBTOTAL 



TOTAL 

♦ 4,719.00 
31,451.00 
31,451.00 
31,451.00 
31,451.00 
31,451.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
22.278.00 
22,278.00 
22,278.00 
22.278.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
22,278.00 
23,942.00 
36,932.00 
5,436.00 
21,883.00 
112,000.00 
130,473.13 
32,000.00 
46,763.43 
3.619.00 

$2,087,2'«.56 



$ 410,202,00 

32,939.00 

32,939.00 

32,939.00 

32,939.00 

5,668.00 

5,668.00 

27,540.00 

46,438.00 

14,982.00 

650.80 

650.80 

650.80 

650.80 

650.80 

9,610.00 

224,000.00 

130,273.13 

32,000.00 

93.526.87 

$1.134.918.00 



TOTAL ALL PHASES 42- INCH HEAT SHIELD 



$1,134,918.00 



M)8 



ORSGSMAL FAOE lii 
OF POOR QUALITY 



TABLE CXXXIII 



TASK M - (01) PER VEHICLE LOGISTICS COSTS (NASI -12500/1 51 00) 



PART NUMBER 

1/2" 00 AMS3195 
139^-020-01-01 
*15375 
5-565-N304-7 
5-565-N30't-7 
688-3-3TC 
688-3-3TC 
AN-6227B-7 
AN-6227B-52 
AN-6227B-71 
AN-6227B-77 
AN-623OB-I6 
AN-623OB-36 
ARP568-902 
ARP568-905 
BO8OI5-OI-OI 
DM5300-1912P-006 
MS28775-OO9 
MS28775-OIO 
MS28775-OI6 
MS28775-112 
MS28775-I29 
MS28775-136 
MS9021-159 
MS902 1-232 
MS9068-0n 
M$9068-012 
MS9068-2't8 
NASI 595-3 
NASI 595-8 
R42653 
R42692 
PMl-7 
PM3-6 
PM05-7A 
PMI5-8 
PM1-7 
PM05-7A 
35% H2O2 
90% H2O2 
HIS-SN7313-2B 
23-002051-2 
23-002052-1 
23-002850-1/-2/-3/- 
23-003283-1 
23-003293-12 
23-003293-12 
23-003365-15 
23-00't098-1 
23-00't271-1 
23-004272-1 
23-000127-1 
23-002588-2 
23-002981-8 
23-002983-1 
23-002983-2 
23-002983-3 
23-0031'»7-1 
23-003793-1 



NOMENCLATURE 



Si 1 icone Cord Seal 

Fourth-stage Module Timer Battery 

Battery 

0-Ring (Antares MB) 

0-Ring (Alcyone I A) 

0-Ring (Antares IIA) 

0-Ring (X-258) 

0-Ring (Antares IIA Nozzle) 

0-Ring (Algol I IB) 

0-Ring (X-258 Nozzle) 

0-Ring (Antares IIA Igniter) 

0-Ring (X-258 Igniter) 

0-Ring (Antares I IB Igniter) 

0-Ring (Altair III Pr. Port Plug) 

0-Ring (Altair III Initiators) 

Algol I I I Nozzle Seal (Bal I) 

Connector (for 23-002588 Battery) 

0-Ring (Antares IIA and I IB) 

0-Ring (Castor I l) 

0-Ring (X-259) 

0-Ring (Castor I I) 

0-Ring (Castor II) 

0-Ring (Castor I I) 

0-Ring (Altair I I I) 

0-Rrng (Altair III) 

0-Ring (For PCI 9-009 Cartridge) 

0-Ring (Castor II) 

0-Ring (Castor I I) 

0-Ring (For PC19-009 Cartridge) 

0-Ring (Algol II and III, Castor) 

Castor Nozzle Closure Plug 

Castor II Pyrogen Ring 

Battery Cel Is (Std.) 

Battery Cel Is (Std.) 

Battery Cel Is (Std.) 

Battery Cel Is (Std.) 

Battery Cells (5-stage Vehicle) 

Battery Cells (4th Mod. Ign.) 

RCS Fuel (Vol. II Maintenance) 

RCS Fuel (Fit.) 

Separation Nut 

Base A 28-volt Battery (Assembly) 

Guidance 28-volt Battery 

k N2 Regulators 

Guidance 37-volt Batteries 

Autodestruct Battery 

Autodestruct Battery {k/kth Mod. Ign.Syst.) 

C/D and Radar Beacon Battery 

Fourth Module T/M Battery 

P /L Sep. & Despin Syst. Bolt Cutter g. Bolt 

Clamp Bolt 

Destructor Union 

Ign./Destr. Battery (E.P.) 

"D" Sep. Explosive Bolt (Holex) 

0.6 KS40 Spin Motor 

1 .0 KS^tO Spin Motor 

1 KS75 Spin Motor 

Destructor 

Initiator (Algol and Castor) 



PER 


LOAD COST 




VEH. 


(EACH) 


YEAR BOUGHT 


100" 


$ 33 


1978 


2 


200 


1973 


2 


12 


1977 


2 


12 


1977 


2 


10 


1970 


2 


10 


1970 


1 


3 


1976 


1 


2 


1974 


1 


5 


1976 


2 


7 


1976 


1 


3 


1976 


1 


6 


1976 


h 


5 


1973 


k 


5 


1974 


1 


100 


1976 


2 


65 


1975 


2 


3 


1975 


2 


2 


1973 


2 


3 


Unknown 


2 


3 


1974 


2 


4 


1974 


2 


4 


1974 


1 


3 


1974 


1 


3 


1976 


2 


4 


1974 


2 


4 


1974 


2 


12 


1974 


2 


8 


1974 


6 


8 


1974 


1 


500 


1974 


1 


20 


Unknown 


202 


29 


1977 


80 


42 


1977 


64 


25 


1977 


22 


80 


1977 


280 


29 


1977 


96 


25 


1977 


1 


150 


1977 


3 


300 


1977 


4 


335 


1971 


1 


1,437 




1 


975 


1971 


2 


5,000 


1977 


1 


425 




4 


477 




6 


477 




3 


501 




1 


1.135 


1971 


2* 


175 


1975 


2* 


125 


1975 


2 


340 


1973 


2 


1,900 


1976 


4 


485 


1974 


-.•r 


1,615 


1971 


.•. 


2,250 


1974 


A 


2.660 


1974 


2 


200 


1973 


4 


464 


1977 



•<iuantity per vehicle determined by payload requirement. 
-^v-Alternate for 13948-020-01-01. 
Total of four spin motors used. 



ORIGli^JAL PAGE tS 
OF POOR QUALITY 



U09 



TABLE CXXXIII Concluded - TASK M - (01) PER VEHICLE LOGISTICS COSTS (NASI -12500/1 51 00) 



PART NUMBER 



NOMENCLATURE 



5M0050-1-1 FW4S Chamber Protective Plug 

5M0060-1-1 FW4S Nozzle Plug 

#8g64 Switch 

#8g65 Switch 

X258-B1-2-05-0032B X-258 (Navy) Igniter 



23-004181-1 

23-004181-2 

23-004180-1 

23-004180-2 

23-004179-1 

23-004179-2 

23-004177-1 

23-004177-2 

3398B6 70055-1 

PCI 9-021 

PC 19-31 

PC33 

SD60A1 

SD60A1 

SD60E0 

SEB26100001-211 

SOI -266-4 

23-004112-1 

71-339510-6P 

71-339512-10P 

71-339514-18P 

71-339518-30P 

71-339520-16P 

71-339522-36P 

72-339512-8P 

72-339516-26G 

72-339520-39G 

72-490 703-8P 

72-490703-1 OP 

72-490704- 18P 

72-490705-23P 

72-490 705-26P 

72-490 706-2OP 

72-490706-32P 

72-490 707-24P 

72-490 707-39P 

72-490707-41 P 

83136DOOOO2-OO3 

CA3101E28-21S 

CA3101E28-21SW 

CA3101E26-10S 

CA3101E36-10SW 

CA3101E36-1OSX 

CA31O1E36-10SY 

K749 

K750 

PT01E-22-21SW 

83136DOOI39 

2-318091 

■,v*2 12059 

'W;2 12060 
23-002667-2 

##23-003352-1 
23-003530-1 
23-004149-2 
AN-6289-4S 
AN-6289-6S 
AN-6289-8S 
AN-6289-IOS 
BR28458-51E 



Destructor 

Destructor 

Destructor 

Destructor 

Destructor 

Destructor 

Safe Arm Unit (Stages 1 and 2) 

Safe Arm Unit (Stage 3) 

Heat Shield Cartridge 

Explosive Cartridge 

200 Series E Separation Cartridge 

200-Series E Separation Cartridge 

Initiator (Altair III) 

Initiator (X-258) 

Initiator (Antares I lA) 

Initiator (Antares MB) 

Initiator (Alcyone lA) 

"E" Sep. Band Nut Assembly 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special "E" Section Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Antares MB Nozzle Closure Plug 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Special Payload Connector 

Thermistor, "B" Section, RCS Instrument 

Thermistor, "D" Ambient Temperature Meas. 

Special payload Connector 

X-259 Nozzle Retainer Ring 

Algol II Nozzle Seal 

Motor Valve Mesh Catalyst 

Motor Valve Mesh Catalyst 

Vehicle Balance Weights 

0-500-pound Transducer 

Al inement Target 

FW4S Initiator Adapter 

X-258 Nut 

X-258 Nut 

X-258 Nut 

X-258 Nut 

Castor I I Pyrogen Gasket 



■"''Special requirement dependent upon spacecraft requirements. 
-.■"'.•Vehicles 208-217. 

#Phase VIII. 
##Vehicles 192, 198, 199. 



PER 


LOAD COST 




VEH, 


(EACH) 


YEAR BOUGHT 




$ 15 


Unknown 




10 


Unknown 




216 


Unknown 




216 


Unknown 




8,000 


1967 




350 


1973 




350 


1973 




350 


1973 




350 


1973 




350 


1973 




350 


1973 




4,000 


1974 




4,000 


1974 




162 


1977 




240 


1975 


2 


240 


1977 


2 


230 


1974 


2 


968 


1977 


2 


968 


1977 


2 


525 


1971 


2 


200 


1974 


2 


145 


1974 


2 


590 


1972 


1* 


110 


Unknown 


1* 


106 


Unknown 


1* 


110 


Unknown 


1* 


110 


Unknown 


1* 


110 


Unknown 


1* 


130 


Unknown 


1* 


110 


Unknown 


1* 


120 


Unknown 


1* 


95 


Unknown 


1* 


250 


Unknown 


1* 


250 


Unknown 


1* 


250 


Unknown 


1* 


275 


Unknown 


1* 


275 


Unknown 


1* 


300 


Unknown 


1* 


300 


Unknown 


1* 


300 


Unknown 


1* 


300 


Unknown 


1* 


300 


1974 


1 


150 


Holding 


1* 


50 


1974 


1* 


50 


1974 


1* 


50 


1974 


1* 


50 


1974 


1* 


50 


1974 


1* 


50 


1974 


1 


143 


Unknown 


2 


63 


Unknown 


1* 


50 


1974 


1 


2.770 


1977 


1 


204 


Unknown 


13 


300 


1974 


5 


300 


1974 


3 


40 


1978 


1 


648 


1977 


1 


2 


Unknown 


2 


135 


1978 


10 


10 


Unknown 


10 


10 


Unknown 


10 


10 


Unknown 


10 


10 


Unknown 


1 


12 


1977 



410 



TABLE CXXXIV - TYPICAL ANALYSIS OF TASK T USING TASK T OF NASI -15000 













PHASE VI 11/5 






MAN MONTHS 


. 


MAN MONTHS 


Teledyne 






21.83 






Hercules Bacchus 






2.00 






Algol III 






9.9 




9.9 


Altair III 






6.7 




2.1 


Castor 






10.65 




5.325 


Edler/Altair Nozzle 






6.54 




2.1 


Edler/Castor NozzI 






3.0 




3.0 


Walter Kidde 






13.65 




6.825 


Honey we 1 1 






15.55 




7.78 


West Coast Subs 






23.5 




23.5 


LTV Special Rover 






8.75 




8.75 


Elkton/Antares III 






9.0 




4.5 


HITCO 






3.0 




1.5 


SAI 






4.0 




2.0 


Teledynamics (TM) 






7.0 




3.5 


WASATCH/Antares 1 1 1 






9.0 




4.5 


TOTAL 


154.07 


85.28 


Current Contract 






139.0 




18.1 (Non-Motors) 


FUTURE 






15.07 




62.18 (Motors Only) 


Contracted Hours 


Enq 


ineerinq Qual 


ity 


Res. Reps. 


Contracted Hours 




5700 


2540 


(139 Man Months) 


Cost 


$67,032 


$23 


419 


$527,505 


Overhead 


65,691 


44 


028 




Travel 


12 


.277 


12 


000 




Reproduction 


2 


,642 


3 


000 




G & A 


29 


,135 


16 


148 


100,226 


Profit 


14 


,197 


7,868 


48.839 




$196,674 


$109,003 


$676,570 


TOTAL: $982,247 


Eng. 


&Qual.: $305,677 





(Revised 533): $971,677 



$295,107 
$971,677 (Contractual T) 

$295.107 (Eng.& Qual.) x 62.18/139 = $132,013 

676,570 (Res. Rep.) X 77.75/139 = 378,406 



Guidance (est.) 
Antares III (est.) 
Castor (est.) 
Additional Res. Reps, 
Phase VIII Vehicles 



68,000 (10) 

292,000 (10) 

162.750 (10) 

80,000 (15) 

445,125 (5) 



34,000 

146,000 

81,375 

40,000 

445 , 1 24 



TOTAL 



$1,256,918 



^11 



TABLE CXXXV(a) - PRORATION OF NAS1-12500 TASK N 



ESTIMATED Fl 


NAL COST 


$3 


.951 


,700 






Launches 


Date 




NASA 


jwl 


NASA (V) 


DOD (V) 


S-188 


3-8-74 










UK-X4 




S-191 . 
S-186 


6-3-74 
7-16-74 










Hawkeye 
AEROS-B 




S-189 


8-30-74 










ANS-A 




S-195 
S-196 


io-n-75 

12-5-75 










DAD 


TIP-II 


S-179 
S-193 


5-22-76 
6-18-76 




GP- 


•A 






AF-P76-5 


S-197 


9-1-76 












TIP-IM 



TOTAL 



Vought proposal quotes 12 to launch from W. to V. = $10,572 each 
Using 7-1/2% profit and 8 VAFB launches =90,919. (8 x 11,365) 

Using analysis from Vought proposal, it takes 9.728 hours to launch a Scout; 

1 oon^r^,^'^ = 5.067 Man Years 

1 ,920 hrs/man yr 

From Vought proposal Manpower TASK N: 

1.225.791 X 1.075 ^ $41,179 

Therefore, 5.O67 x $41,179 = $208,654 (cost per launch) 

Assume same cost at Wallops, therefore 9 x 208,654 = $1,877,886 

Assume 10 at Wallops and 27 at VAFB (includes 7 men added by modification). 

Total - $3,922,000 

Travel - 90,919 

Per Launch Cost - 1,877.886 

3 year Maintenance Costs - $1,953,195 

iO/37 X 1,982,695 = $527,690 WFC 

27/37 X 1,982,895 = $1,425,305 VAFB 



412 



TABLE CXXXV(b) - PRORATION OF NASI -12500 TASK N (Continued) 

50% D.O.D. = $712,652 
50% NASA = $712,653 

NASA-WFC = $527,890 
NASA-VAFB = $712.653 

(Ma int.) TOTAL NASA $1,240,543 

1/3 X $1,240,543 = $413,514 per Year (NASA) 
J/3 X $712,652 = $237,551 per Year (D.O.D.) 
1/5 X 712.653 = $^k2,53^ per NASA Foreign Launch at VAFB 

-TASK N SUMMARY 

UK-X4 142.531 + 208,654 + 11,365 = $362,550 

AEROS-B 1/^2,531 + 208,654 + 11,365 = $362,550 

NASA(V) 3(208.654 . 11,365) . (712.653 - 2(142.531) = $1,087,648 

NASA(W) 208.654 + 527.890 = $ 736,544 

NAVY 2(208,654 -. 11. 365) + 712,652 = $1,152,690 

A.F. (208.654 4. 11.364) = $220.018 

'^^'^'^^ $3,922,000 



NASA Unit Price = 2,549,292 ^ 6 = $424, 



882 



■Does not include costs of launch supplement fr 



om TASK H. 



TABLE CXXXVI - TASK N - FIELD TEAM SUMMARY 



Contract 


Phase IV 


Phase V 


Phase VI 


NASI -12500 






(2) 
$ 719.253 
487,868 
220,024 


NASA 
Navy 
Air Force 






NASI -10000 






1,56 3,340^'^ 
1,475,936 


NASA 
Navy 


$ 313.667 


$ 938,00i» 


NASI -7256 








NASA 
Navy 




1,189,144 





NASI -6020 








NASA 
Navy 


970,309 
Direct 


968,099 
Direct 




NASA Share of DOD Contract 








FY 1967 
FY 1968 
FY 1969 
FY 1970 


155,152 
164,200 


158,350 
172,169 




NASI -15000 








NASA 








Navy 






726,911 


TOTAL NASA 


$1,603,328 


$3,425,766 


$2,282,593 


TOTAL DOD 


Direct 


Direct 


$2,910,739* 


UNIT NASA 


$160,333 


$244,698 


$207,509 


UNIT DOD 






$727,684 



^Additional funds may be required to complete. 

(1) Includes ESRO IV 

(2) Includes IJKX4 g, AFRO$-B 



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ORIGINAL PAGE ^S 
OF POOR QUALITY 



TABLE CXXXVI I I (a) - 



Propel lants 

Photo Squadron 

PMEL & CCF 

Misc, Base Supply Hardware 

Misc. GSA/DSA Items 

Purchases Under $500 

Purchases Over $500 (Listed Below) 

CCTV Installation 

Misc. GBL's 

Imprest Fund Purchases 



TOTAL 



My 






- MSO-WTR 


EXPENDITURES 




SUMMARY 


FY 76 


FY7T 




$ 2,293.7^ 


$ 361.70 




5,8^+3.00 


479.93 




10,575.00 


3,000.00 




930.00 







5,622.39 


2,078.97 




19,034.03 


4.353.44 




28,830.^+5 


1,848.53 




28,000.00 







785.63 







600.02 
$102,514.26 







$12,122.57 



DETAIL LISTING OF FY76 PURCHASES OVER $500 



Reduce, Print & Bind Scout Schematics Eng. Serv. on ECS 

Air Conditioning Units 

Freon for ECS Air Conditioning Units 

Printing Calculator for Spin Balance 

Air Lift Work Platforms (for VAFB and WFC) 

Portable Vacuum Pump 

RTV 88 

Engineering Services and Warranty Validation on OSB Air Compressor 

Xerox Card Printer Rental 

Super Clean Nitrogen Gas 

RTV 88 

Aluminum Plate and Structure for Shelter Work Platforms 

Structural Steel for Shelter Work Platforms 

RTV 88 

Polarized Antenna and Reflector 

ECS Ducting 

RTV 88 

Engineering Services on Cosmodyne Unit 

RTV 88 

RTV 88 

RTV 88 

Xerox Card Printer Purchase (Credit received for previous 

rental payment) 
Electronic Flowmeter 



TOTAL 



$ 868.65 

3,000.00 
841 .80 
648.00 

9,998.00 
688 . 70 
502.56 
580.00 

2,025.00 
650.64 
502.56 

2,526.74 
541 .62 
651.00 
591.70 

1,100.84 
651.00 
749.00 
542.34 
651.00 
519.30 

7,405.00 

2.220.00 
$28,830.45 



FY7T 



RTV 88 



$1,848.52 



k^8 



OF POOR 



TABLE CXXXVIIl(b) - MSO EXPENDITURES - SUMMARY SHEET, FY 1977 



ITEM: 

Propel lants 

Photo Squadron 

PMEL & CCF (See Note 1) 

Misc. Base Supply Hardware 

Misc. USA/GSA Hardware 

Purchases Under $500 

Purchases Over $500 (Listed Below) 

Misc. GBL's 

Imprest Fund Purchases (See Note 2) 



$ 



811.31 

2,837.72 



725.98 

it, 7^8.86 

21,510.59 

36,9^3.71 

212. it9 





TOTAL 

NOTE 1 : 
NOTE 2; 



$67,790.66 



Beginning FY77, this Item is a Range charge against EOD^O. 
Imprest fund buying capability no longer available to MSO. 
This item is, therefore, included in Purchases Under $500. 



LISTING OF FY77 PURCHASES OVER $500 



DESCRIPTION 

T/M Receiver Repair 

CCTV Pan Tilt Heads 

Terminals for T/M Data Display System 

Interface Cards for Above Terminals 

Lambda Power Supplies 

Micro-wave Equipment for Data Display System 

RTV-88 

Reduce, Print and Bind Scout Functional Schematics 

Video Tape Read-out Equipment 

Micro-wave Equipment for Data Display System 

Adhesive Foil and Tape 

Air Log Dol ly Parts 

Shelter Door Repair 

Fork I ift Repair 

Data Graphix Terminal 



AMOUNT 

$ 1,245.00 
1 ,67^.00 
3,390.00 
2,025.00 
760.00 
9,890.00 

2,037.^ 
759.20 

2,024.35 

2,850.00 

646.68 

558.00 

756.00 

3,878.00 

4.450.00 



TOTAL 



$36,943.71 



M9 
TABLE CXXXVIIl(c) - MSO EXPENDITURES - SUMMARY SHEET, FY 1978 



HEM : 

Propel lants $ 1,019.16 

Photo Squadron 't, 853. A3 

Misc. Base Supply Hardware 2,537, H 

Misc. USA/GSA Hardware 6,325.52 

Purchases Under $500 3't,083.94 

Purchases Over $500 (Listed Below) 5,87't.25 

Misc. GBL's 638.82 



TOTAL $ 55,332.26 

LISTING OF FY78 PURCHASES OVER $500 
DESCRIPTION 

Repair Fairbanks Scales 

Connectors 

Thread Gauges 

RTV-88 

Tubing 

RTV-88 

Diametrics 

TOTAL 



The NASA Scout Project Office Range Resident supervised all the require- 
ments by the field personnel. Table CXXXVII lists typical obligations 
by LTV for VAFB through 1978. Table CXXXVII I are the requirements that 
were filled through G.S.A. and Scout Project Office. Table CXXXIX 
itemizes costs for ground support equipment. DCASO assessments are 
listed in table CXL. Shipping costs are listed in table CXLI. 

Scout improvements were continuously being programmed for the next 
hardware purchase and Phase VI improvements are shown in table CXLI I . 
The special R&D funds (I8O) program costs are listed in table CXLI II. 



AMOUNT 


$ 


951.00 




703.82 




501.10 




1,344.60 




502.23 




1,368.00 




503.50 


$ 


5,874.25 



420 



OF 







TABLE CXXXIX 


WALLOPS 






FY72 FUNDS 
LTV 

Others 
Subal lotment 


$ 




5^.20 

73,225.86 


FY73 FUNDS 
LTV 

Others 
Subal lotment 






6,912.08 

20'».625.33 


FY7'» FUNDS 
LTV 

Others 
Subal lotment 




1,077.08 




FY75 FUNDS 
LTV 

Others 
Subal lotment 






2,600.00 

49,985.7^ 


FY76 FUNDS 
LTV 

Others 
Subal lotment 


$ 




2,it00.00 

315,000.00 


FY7T FUNDS 
LTV 

Others 
Subal lotment 


$ 







FY77 FUNDS 
LTV 

Others 
Subal lotment 


$ 




1.827.92 

V99.982.OO 


FY78 FUNDS 
LTV 

Others 
Subal lotment 


$ 




69.95 
100,000.00 


FY79 FUNDS 
LTV 

Others 
Subal lotment 











$ 


957,760.16 



- GSE EXPENDITURES 



WTR 



FY72 FUNDS 
Others 
Subal lotment 

FY73 FUNDS 
LTV 

Others 

Subal lotment 
(Microwave Equip. 
$20,000.00) 

FY7^ FUNDS 
LTV 

Others 
Subal lotment 

FY75 FUNDS 
LTV 

Others 
Subal lotment 

FY 76 FUNDS 
LTV 

Others 
Subal lotment 

FY7T FUNDS 
LTV 

Others 
Subal lotment 

FY77 FUNDS 
LTV 

Others 
Subal lotment 

FY 78 FUNDS 
LTV 

Others 
Subal lotment 

FY79 FUNDS 
LTV 

Others 
Subal lotment 



$ 520,148.61 

135.26 

49,669.39 



20,059.00 
116,247.54 
122,712.32 



260,713.15 
130,380.78 



9,5^9.50 




299*826-50 
99.^75.77 









481,706.25 



61 ,500.00 



6.529.01 







$2,178,653.08 



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o_izzzzzz 



1*23 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLE CXLI(b) - SCOUT SHIPPING EXPENDITURES Concluded 



PKOGKAM I BO 

HO siioozioa 

N«SI-725( 

NASI-92M 

HAS I -92 58 

HASI-IOOOO 

HASI-I0U3 

HASI-10988 

PROGKAII HSO 

L-Uik — 

L-13'l97A 
1-23*9 lA 
L-46232 
l-WOOl 

1.-58203A 

L-e8203A 

L-75t*3 

L-77088 

1-8*994 

L-S58113 

L-97050 

LX-72053 

LX-72061 

LX-730*7 

HAS I -3*93 

HAS I -3*98 

HAS I -3698 

HAS I -* 79* 

HASI-A795 

HAS 1-5592 

HASI-5610 

HASI-5880 

HASI-5883 

HAS I -6020 

HAS 1-6378 

N.UI-6868 

HASl-6935 

HASI-7102 

HASl-7199 

HASI-7256 

HASl-025« 

"'^1-9325 

HAS I -9597 

HASl- 10000 

HASI-I0i72 

HASI-10*8I 

HAS! -10*82 

»AS1-I0*83 
HASl -10*8* 
MAS I- 10500 
HASI-1|I|00 
HAS1-II859 
NASI-11867 
NASl-12500 
HASI-MOOO 
NASl-13100 
HAS1-1*200 
H/iSl -1*500 
HAS1-1**19 
HAS1-I*S50 
HASl-15000 
NAS1-15100 



Through 

" 'V fUaZi " '973 FT 187* FT 1975 FY 1976 FY I97T 

i 5.15 

13.90 
28.05 
57.90 
6.55 

"•28 $ 63.95 J 12.90 

$ 19.30 

21.00 



FY_!2ZZ_ 



FY 1978 



33.50 
2,760.00 



S *3.62 



$ 326.55 
8.91 



I,I6*.80 
1.115.96 



2.526.00 












1,090.00 




7.82 






267.53 




325.3* 






167.90 
















2.75<.*0 






12.90 










21.130.32 
















27. *0 
















2,020.05 
















2,592.00 
















1.00 
















52,6I8.*3 
















M*,*90.05 
















8,128.02 
















21,939.21 
















288.39 






72. *3 


838.00 


1 .827.28 






li.u> 
















e,975.*7 






*6.72 










6,290.19 
















56,095.86 
















110,912.17 


7,3*0.72 


1,62*. 93 










*,788.20 


3. 595, 


.21) 


5,*01.96 


2,136.39 


1,026.28 


289.00 




136.80 








71.50 


65.20 


**1.00 




98,1*8.56 


7.100, 


.79 


**,292.87 
316.75 


3,1*2.*9 


9.75 


-1,*3*.97 




6,812.43 






51. Ml 




M.5* 


s 


"6.59 
365.37 


10.50 






716.20 


6,056.69 


1,566.13 


107.73 




78.39 






38.22 










7,679.0* 






17.835.61 
11. *9 


290.13 


6,777.02 
16.51 


1.1*5.81 










8,892.51 


10, 16*. 19 


168,059.58 

1,631.56 

*07.*6 


21,*37.63 15 
*.3*6.2* 1 


,106. *8 
,210.11 



65. *6 



I*. 398.6* 



2,030,*7 



320.15 
5.988.59 



3,6*3.80 
86*. 00 



2,057.08 

I1.*3 

1,090.85 

2,006.68 

*2,263.2* 

I*, 1*3. 05 



2, 
21, 



($2*5.68) 
5.85 
13.90 
28.05 
57.90 
6.55 
93.13 
19.30 
21.00 

($1,002,135.60) 
*3.62 
326.55 
8.91 
33.50 
2,760.00 
1,16*.80 
1.115.96 
9.*5 
13.88 
3.616.00 
7.82 
325.3* 
267.53 
167.90 
12.90 
75*. *0 
130.32 
27.*0 
2,020.05 
2,592.00 
1.00 
52,6l8.*3 
11*,*90.05 
8,128.02 
21.939.21 
3.091.56 
12.05 
9,022.19 
6,290.19 
56,095.86 
"9,877.82 
17.237.03 
273.50 
**1 .00 
151. 229. *9 
316.75 
7.137. S* 
3,6*3.80 

1.229.37 

8,*57.25 

116.61 

33,727.61 

16.51 

II .*9 

236,981 .02 

1 ,631.56 

8,020.89 

2.030.*? 

r*.*j 

1,090.85 

2,006.68 

*2,583.39 

20,131.6* 



PROGBAH *97 
HAS|-J*S3 
HAS 1-3698 
HASl-4325 
HAS I -479* 
HASl-5592 
HAS I -56 10 
HASI-5880 
KAS 1-5883 
HAS 1-6020 
HASl-6935 



15.65 

509.12 

670.3* 

3,302.00 

ll.*5 

6,6*2.29 

637.50 

6,388.11 

11.912.69 

1,017.22 



(531,106.37) 

15.65 

509.12 

670.3* 

3,302.00 

11 .*5 

6.6*2.29 

637.50 

6 ^88 1 1 

"!912.69 

1,017.22 






0R1G8NA1 FA' 

OF POOR QUALITY 



TABLE CXLII - IMPROVEMENTS - PHASE VI (178-192) 
490-01-04 CHANGES 

SS Requirements - 

Fourth-Stage Instrumentation Ring 

490-02 CHANGES 

VEHICLE CHANGES 

Apollo Standard Initiators 

Autodestruct Module 

Azimuth Al inement Tool 

Cartridge Insertable Explosive Bolts 

Deleted Base "A" Hydraulic Pressure Switch 

Fin Tips - Large Area 

First-Stage Harness 

42- Inch Heat Shield 

Improved H2O2 Components 

Jet Vanes - Shape Material 

Linear Shape Charges 

Lower "D" Section Rearrangement 

Middle "D" Section ReJ^sign 

New H2O2 Bladders 

Power Control Relay Box 

Roll and Yaw Compensation Unit 

Safe/Arm Units 

S-Band T/M Transmitter and Lightweight T/M Package 

Separation Systems - 200 Series and EG Series 

Spin Electrical Connection 

GROUND SUPPORT EQUIPMENT 

Apollo Standard Initiator Addition 
Autodestruct Module Modification 
Azimuth A 1 inement GSE Modifications 
Cartridge insertable Explosive Bolt Revision 
Linear Shape Charge Modification 
Power Control Relay Box Modification 
Roll and Yaw Compensation Unit Addition 
S-Band Telemetry Modification 
Spin Motor Connector Modification 

NEW PROPULSION 

Algol MB Nozzles - Rebuilt 

High Pressure X-25'' (Third Stage) 

490-03 CHANGES 

Algol I I I (First Stage) 



k2^ 



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TABLE CXLIV - NASI -10^1 (CONTRACT HISTORY) 
HERCULES INCORPORATED 
X258 Rocket Motor Studies 

Est. Cost Fee Total 



Contract (Funded) {Ik Months) 

Task I Support X258 Shelf Life Extension 

Task 2 Hydrotest X258 Chamber 

Task 3 Pack & Ship (2) X259 Igniters 

Task 4 Insert Helicoils in (2) X259's 

MOD-1 Change of Manhours 

MOD-2 12 Mos. Extension to 36 Mos, 

MOD-3 12 Mos. Extension to 48 Mos. 

MOD-4 New Scope 

MOD-5 12 Mos. Extension to 60 Mos. 

MOD-6 Government Owned Property Reporting 
Task 5 Pack & Ship (2) X248's 
Task 6 Inspect & Test Fire {k) X259's 
Task 7 Pack & Ship X259 Motor 
Task 8 Clean & Ship (2) X259 Chambers 

Task 9 Static Fire R & H Motors w/Ceramic Inserts (5,500) 
Task 10 X-258 H.E. Feasibility Study 
Task 11 Transfer Scout Tooling 
Task 12 Dispose of GFP 
Task 13 Adv. ^tth Stage Design Optimiz. Studies 

MOD-7 24 Mos. Extension to 84 Mos. 

MOD-8 Extension Completion Date 

MOD-9 Schedule Change 
TOTAL 

Total - Assigned Tasks 

Unasslon^rf 
( )Assigned Tasks Budgetary 



$ 93,020 


$ 6,976 


$ 99.996 


(2,000) 






(9.100) 






(300) 






(10,600) 

































69,767 


5.233 


75,000 




















(800) 






(31.300) 






(1,950) 






(1,500) 






ts (5,500) 






(33,100) 






(690) 






(1,370) 






(48.615) 






134.998 


10.800 


145.798 




















$297,785 


$ 23.009 


$320,794 


(146.825) 






(150.960) 







427 

TABLE CXLV - NASl-10482 (CONTRACT HISTORY) 

THIOKOL CORPORATION/HUNTSVILLE 

Castor Motor Studies 

Est. Cost Fee Total 

Contract (Funded) (12 Months) $ 91,697 $ 6,877 $ 98,57** 

MOD-1 12 Mos. Extension to Zk Mos. 

Task 1 Review and Evaluate NOT Methods (5,600) 

Task 2 Preparation Castor II Drawing and Spec. Trees 

MOD-2 12 Mos. Extension to 36 Mos. 

MOD-3 12 Mos. Extension to 48 Mos. 

MOD-4 12 Mos. Extent ion to 60 Mos. 

MOD-5 Government-Owned Property Reporting 

MOD-6 Increased Efforts in Review and Evaluate 95,902 7,193 103,095 
NOT Methods 

MOD-7 Administrative Change 



MOD-8 Administrative Change 







MOD-9 Schedule Change 



TOTAL $187,599 $1'»,070 $201,669 



Each motor contractor negotiated a task contract to support the motor 
production and processing. Tables CXLIII through CXLVII list these 
contracts. NAS1-10485 is omitted as only one first-stage Algol II was 
used in Phase VI . 

Tables CXLVII through CLI depict many special contract items as major 
developments to minor modifications. Many of these can be found as a 
separate report in Appendix M. 



428 

TABLE CXLVI- NASI -10^*83 (CONTRACT HISTORY) 
HERCULES INCORPORATED 
X-259 Rocket Motor Studies 

Est. Cost Fee Total 
Contract (Funded) (12 Months) $ 93.172 $ 6,522 $ 99,694 

Task 1 Review and Evaluate NOT Methods 
Task 2 Review X-259 Inspection Reports 

Task 3 Study Extens. Shelf & Service Life X-259-B3 
Motor 

Task k Preliminary Inspection 4th Stg. Motor (4,693) 
and Improved X-259 Motor 

MOD-1 12 Mos. Extension to 24 Mos. 

Task 5 Improved Igniter for X-259 Motor 

MOD-2 Increase in Manhours and Materials 45,004 3,150 48,154 

Task 6 X-259 Rocket Motor Analysis (114) 

Task 7 Delivery of One X-259 Igniter 

MOD-3 12 Mos. Extension to 48 Mos. 

MOD-4 Additional Technical Support 70,091 4,909 75,000 

Task 8 X-Ray X-259 Motor HIB-215 (1,593) 

MOD-5 12 Mos. Extension to 60 Mos. 

MOD-6 Government Owned Property Reporting 

Task 9 Packing, Crating, and Shipment of Tooling 

Task 10 Design Optimization Study Advanced 
Third-Stage Motor Chamber 

Task 11 CY1 Propel lant Relative Quickness Test (2,837) 

Task 12 Shipment Government Owned Tooling 

Task 13 Estab. Cast Date Antares I IA Igniters (1,821) 

Task 14 Packaging and Shipment X-259 Motors (7,590) 

MOD-7 2'j Months Extension to 84 Months 119,258 8,944 128,202 

HOD-8 Extension Completion Date 



^^^^'^ ^327,52> $^3.52;, ^351,050 



if29 



TABLE CXLVII- NAS1-1048if (CONTRACT HISTORY) 
UNITED TECHNOLOGIES CORPORATION 
Algol lie Nozzle, Algol III and FW4-S Motors Studies 



Est. Cost 



$ 92,360 



Contract (Funded) (12 Months) 

Task 1 Evaluate NOT Methods/ Inspect. Criteria 
for Algol III and FW-4S Motors 



Task 2 Eval. High Energy Storable Hybrid Propel lants 

MOD-1 Appropriation and Allotment Change 

Task 3 Provide FW-^S Motor Case Samples 

Task k Audit F\l-kS Motor Prod. History and 
Re-X-ray of Motor 

Task 5 Provide Drawings of Government Owned Tooling 

MOD-2 Additional 12 Mos. Effort 38,000 

MOD-3 10 Mos. Extension to 34 Mos. 

mo-k Additional 6 Man-Years of Effort 271,026 

Task 6 Fabrication Algol III NDT Test Specimens 

Task 7 FW-4S Motor Segment 

Task 8 Tooling FW-4S Motors 

Task 9 Fabrication 5 Altair Motors 

MOD-5 Additional li Man-Year Effort 92,975 

Task 10 FW-4S Nozzle Installation and Alinement 

Task 11 dual. Altair III Igniter with SBAS I 

MOO-6 12 Mos. Extension to 58 Mos. 

MOD-7 Government Owned Property Reporting 

MOD-8 Contractor Name Change 



MOD-9 Correction Contractor Name Change 
TOTAL 







$494,361 



Fee 



6,525 



Total 



$ 6,500 $ 98,860 



2,701 


40,701 








18,974 


290,000 



99,500 









$34,700 $529,061 



430 

TABLE CXLVIII - NASI-IO5OO (CONTKACT HISTORY) 
LTV Aerospace Corporation 

TASK 1 - DESIGN, DEVELOPMENT, QUALIFICATION, AND PRODUCTION OF SCOUT 
PAYLOAD SEPARATION IGNITION TIMERS (9-17-71) 

66.000.052 

66.000.099 
M-1 (Administrative Change) 
M-2 (Timers) 66.000.243 

M-3 (Timers) 66. 000. 'tis 

M-4 (Relays and P.C. Boards) 6600.0513 
M-5 (Mi»-Equi table Adjust.) 6600.0513 

TOTAL -: $309,216 

TASK 2 - PHASE II STUDY OF IMPROVED MATERIALS FOR USE ON SCOUT ROCKET 
MOTOR NOZZLES (10-27-70 



RAS183 


$200 


000 


RASl8i| 


29.847 


RAS184 


30 


580 


R1246 


20 


,791 


E7000Y 


29 


,200 


E7000Y 


-1 


,202 







60.400.876 


RASI79 


$105,335 


M-1 
M-2 


(Nozzle Material 
Investigation) 

(Nozzle Material 
Investigation) 


66.000.220 
66.000.220 


RAS 1 79 
RAS 1 79 


23.300 



M-3 


(Nozzle Material 
Investigation) 


66.000.220 


RAS 1 79 


7.59^ 


M-4 
M-5 


(C.R. Report) 
(Extension Completion 


Date) 




n 





TOTAL $121,041 

TASK 3 - DESIGN, PROCUREMENT, FABRICATION, TEST, AND STORAGE OF A 
SCOUT ATTITUDE CORRECTION SYSTEM {l-lk-Jl) 

66. 000. 0^*2 RASI90 $li»0,000 

66.000.151 RASl8i» l^tS.SOO 

M-1 (Schedule Revision) ' 

M-2 (GFE Air Bearing) 66.000.042 RAS190 -2,227 

M-3 (Extension Completion Date) 

M-4 (Overrun) 66.000.323 K\lki> 47.107 

M-5 (Overrun) 66.000. 36I R1246 60,520 

TOTAL $393,900 

TASK k - DESIGN AND FABRICATION OF LARGE DIAMETER PAYLOAD SEPARATION 
SYSTEM (6-20-73) (E-25) 

66.000.240 RASI96 $182,350 

M-1 (Five Bolt Cutter Assys.) 
M-2 (Icr. Electronic Inter- 
stage Connector Capa- 

bility) 

M-3 (Administrative Change) 

M-4(M-l,M-2) 66.000.326 RI258 37.123 

66.000.331 R1258 5,652 

M-5 (Extension of Completion Date) £ 

TOTAL $225,125 



TOTAL CONTRACT $1,049,282 



i^31 OF POOR QUALHY 

TABLE CXLIX- NAS1-12500, NASI-I5OOO, &NAS1-15100 (68-71) 

STANDARD TASKS 
NASI- 12500 

OSCAR Mission Analysis and Orbital Studies, WA-3381/BFC $ 3,277 

Environmental Study - S-200, WA-3381/BGE 3,800 

Vehicle Interface Drawing - S-192, WA-3381/BHA 463 

Vehicle Interface Drawing - S-195 and S-197, WA-3381/BHE 2,196 

GSE Interface Drawing - S-195 and S-197, WA-3381/BJH 2,759 

Heat-Shield Design - S-192, WA-3381/BKC 923 

Heat-Shield Design - S-195 and S-197, WA-3381/BKF 2,112 

Pref light Planning, S-192, WA-3381/CAD 13,380 

Pref light Planning, S-195, WA-3381/CAH 20,913 

Pref light Review, S-199, WA-3381/CBA 840 

Pref light Review, S-195, WA-3381/CBH 955 

Final Flight Report, S-I78, WA-3381/DDA 36,582 

Heat-Shield Fit Check, S-192, WA-338I/HCC 2,756 

Heat-Shield Fit Check, S-195, WA-338I/HCE 3,223 

Heat-Shield Mod., S-192, WA-3381/HED 18,635 

Heat-Shield Mod., S-195, WA-3381/HEG 22,0M» 

Heat-Shield Mod., S-197, WA-3381/HEH 24,343 

In-plant processing S-192, WA-3381/HFG 140,329 

In-plant processing, S-195, WA-3381/HFJ 184,138 

In-plant processing, S-197, WA-3381/HFL 167,476 

In-plant processing, S-199, WA-3381/HFN 129,467 

In-plant processing, S-200, WA-3381/HFP 28,739 

Launch Support, S-195, WA-3381/HQE 79,021 

Launch Support, S-179, WA-3381/HGG 83,771 

Launch Support, S-197, WA-3381/HGJ 37,08l 

P76-5 Heat-Shield Design, WA-3381/BKH 2,l40 

P76-5 Heat-Shield Design, WA-3381/HEK 26,906 

P76-5 Pay load Dynamic Analysis, WA-3381/BGD 8,743 

P76-5 Preliminary Trajectory, WA-3381/BEF 3,366 

Environmental Study, WA-3381/BDG {S-195) 4.179 

SUBTOTAL $1,054,557 

NASI -15000 

Pref light Planning, S-204, WA-3525/CDAD $ 4,568 

In-plant Vehicle Processing Support, S-204, WA-3525/EAAF 7,000* 

R/S, l^ecert, B/U, MFC, C/0, S-204, WA-3525/HAG 173.000^ ''- 

SUBTOTAL $184,568 



'^Estimate. 



0RIGl^5AL PAdE [S 
^32 OF POOR QUALITY 

TABLE CL- NAS1-12500. NASl-15000. &NAS1-15100 (68-71) 

MISSION PECULIARS 

Actuator Rework. S-192 and S-199. WA-3525/EAFA (1/3) $ 13.785 

Actuator Rework. S-204. S-205. and S-206. WA-3525/EAFB (3/5) ^.8^5 

Inspection of AS360F316c6A Fittings. S-192, S-199. S-20U. S-205. 15.980 

and S-206. WA-3525/EAFC (5/11) :.c nnn- 

HoOo Bladder Tank Adhes ion. S-192. WA3525/EAFD (1/2) 35,000^^ 

Vehicle S-199 Special Fourth-Stage Instrumentation. R-75 7 qnb 
Vehicles S-192/199 Heat-Shield Rework, R-22 /'^ 

Vehicle S-192 Fourth-Stage Instrumentation. R-66 ,n QW- 

Vehicles S-192/199 Rework GFE R/Y and Vehicle Retest. R-83 i.oin 
Incorporate Altair ill-A in Vehicle S-199. R-63 i loi 

•S-178 Spin Anomaly. R-I8 ^'[t^ 

Modification to Scout Vehicle S-179. R-'+9 ^ 

Vehicles S-179 and S-192 Guidance Comp., Inspt.. retest. R-91 ^'ici 
Heat Shield Fit Checks (TIP-ll), R-II8 ^'^^j 

Incorporation of accumulated modifications to S-179. R-143 o.'^^i 

Retest of Vehicle S-179 components, R-164 Zii'^qo 

Vehicle S-179 fourth-stage Telemetry System. R-lb3 18 707 
Roll-Yaw Compensation Units , R-160 9 110 

Mod Kit to Dummy Heat Shield, R-I65 (S-179) ^'''" 

Heat Shield-to-Payload Fit Check. R-I65 (S-'79) ^'^/° 

Reprogram and Retest Guidance System, R-165 S-179 tv'qoS 

Vehicle S-179 Payload Coordination and Pref 1 ight Planning. R-I65 77.90a 
Performance Capability Study - TIP-III Mission. R-I8I 3.^3/ 

TIP-n/IM Spacecraft Dynamic Loads Analysis. R-207 T^'^AO 
Vehicle S-192 Third-Stage Motor Change. R-191 ' 



SUBTOTAL 



ifO.983 
16.^0 

$490,006 



"Estimate 
•Phase VI 



OF POOR QUALITY 

TABLE CLI- NASI-I25OO & NASI-I5IOO - DOD TASK R (68-71) 

SPECIALS 



Backup air system for VAFB, R-2 $ 6,745 

X-259 embedded bcxjt strain measurement test, R-8 1,876 

*lncorporate new GFE power supplies into GSE at VAFB, R-12 12,296 

^Install and check out specific GFE-GSE kits at VAFB, R-23 15,554 

*lnstall explosive-proof wiring. Dynamic Balance Facility, R-32 4,392 

•'=Modif ication to D-section cooling air in S^T at VAFB, R-48 2,086 

*VAFB ground support equipment remodif ications, R-64 5,638 

^Backup air supply at VAFB, R-65 26,904 

Environmental control system for Scout payloads at VAFB, R-72 28,742 

Environmental control system for Scout payloads at VAFB, R-83 45,964 

''-Scout GSE Mods for Guidance System Env. Test and SOP, R-92 38,584 

VcPhase Angle Voltmeter at VAFB, S-003 1,483 

Roll and Yaw Compensation Units, R-I60 18,706 

Inspection of X-258 motors, R-202 26,056 

Fabrication of roll and yaw compensation units, R-I98 59,885 

#TRANSAT Heat Shield Mod. and Fit Check, R-11 56,029 

X-258 Nozzle Examination, R-43 59,178 

S-199 Special Fourth-Stage Instrumentation, R-75 32,005 

SUBTOTAL $442,123 



TABLE CLI I- NASI-I25OO &NASI-I5IOO - DOD TASK R (68- 71) 

' VSHELF LIFE 

•Shelf life testing of first and second-stage initiators, R-I6 $ 1,778 

'^Explosive bolts shelf life extension, R-36 1,258 

"Castor II shelf 1 if e extension, R-62 3l|202 

*X-259 rocket motor shelf life extension program, R-74 15,834 

"Extension of TX-463-1 pyrogen shelf life, R-76 2^809 

'-Algol II shelf life extension program, R-88 55,601 

"Procurement of Altair III shelf life materials, R-93 19)479 

Static test firing X-258 motor, R-I38 41 ^420 

^Static test firing Castor IIA, R-195 12^686 

"dual, firing Antares IIA, R-179 24^936 

#X-258 Motor Shelf Life Program, R-16 24^921 

X-258 Igniter Shelf Life Analysis Program, R-I9 (1/2) 4^284 

Aging Study Rept. -Scout Motors, R-99 18^952 

Algol lie Motor Shelf Life, 78-I7 19^000 

Algol lie Igniter Shelf Life, R-86 i3[256 

SUBTOTAL $287,416 



•Phase VI . 

"50 percent NASA, 50 percent DOD. 

^Begins New Contract NAS1-15100- 



435 



CHAPTER 9 - SCOUT PHASE VI RESULTS 



"'"'"■■'= ^^^ ^^ mx ,MM^ 



1*36 



ORlGil^AL PA(r:i IC^ 
OF POOR QUALIW. 



Vehicle 


No. 


n 


iqht 


No. 


Vehicle No. 


Flight 


No. 


Vehicle No. 


180 






83 




181 


88 




186 


183 






8k 




178 


89 




189 


184 






85 




190 


90 




187 


182 






86 




188 


Sh 




179 


185 






87 




191 


102 




192 



The summary of results of the Scout Program is presented in tables CLIll through 
CLV. Each of the Scout Phase VI flights is detailed in table CLIV. Tables 
CLlli and CLIV detail the historical results of Phases I through V. Table 
CLV presents the flight parameters of each launch designated by flight number 
and mission. The Scout flight numbers for the Phase VI vehicles are as follows: 

Flight No. 

75 
78 
79 
80 
82 

Tables CLVI through CLXX present the complete postf light data for each Scout 
vehicle including launch azimuth, launch elevation, motor serial numbers, 
heat-shield specifications, parameters, weight, etc. A few of the Phase VI 
Scouts are presented in figures 119 through 125. 

Tables CLXX! through CLXXXlll present the summary of boost trajectory performance 
for most of the Phase VI launch vehicles. Table CLXXXIV presents a summary of 
conditions at fourth-stage burnout. 

The pitch, yaw, and roll attitude errors are presented in tables CLXXXVII 
through CXCII. These data are telemetered from the output of the inertial 
reference package's miniature integrating gyros (MIG). The second- and third- 
stage attitude errors are usually biased to one side of the control system 
deadband during boost because of thrust misal inement . On all orbital missions 
the pitch and yaw zero-rate deadband is 0.802 degrees, plus or minus 10 percent. 
The roll zero-rate deadband is 1.432 degrees, plus or minus 10 percent. 

The yaw displacement time history for vehicle S-181C includes approximately 
35 percent of the rate gyro output. This anomaly was completely investigated. 

The first-stage pitch program, maximum control surface deflections and all 
transients are presented in table CXCIII. This table also shows configuration 
and control gains for each Phase VI Scout flight. Fit check, jet vane and tip 
data are also included. 

The disturbing pitch, yaw, and roll moment disturbances are presented in 
tables CXCIV through CXCVI. The pitch, yaw and roll attitude error and 
angular rate prior to second-stage ignition are presented in table CXCVI I. 
The rigid body rate changes due to ignition transients and separation disturb- 
ances are also shown with the maximum attitude error and rate attained during 
the control system capture maneuver. The third stage is shown in table CCVIII. 

The time histories by vehicle of second- and third-stage pitch and yaw thrust 
misal inement and moment disturbance are presented in table CCIX. Total thrust 
misal inement by vehicle is shown in tables CCX and CCXI. Tables CCXIl and 
CCXIII show additional pitch and yaw second- and third-stage thrust misal inement . 



437 



OF POOR QUALIIY 



TABLE CLIII(a) - SUMMARY OF RESULTS (Phases I, ||, and III) 
PAYLOADS (23) (5) (7) (2-A.E.C.) 



TOTAL 

1 Allkl^lf^«* 


NASA NAVY AF CONF. 


LAUNCH 
WALLOPS 


SITE 
WTR 


VEH. 
NO- 




LAUNCH 






LAUNCHES 


FY 


DATE 


TYPE 


RESULT 


1 


1 


X-1 


I 




STl 


61-1 


7-1-60 


P 


S 




2 


2 


X-1 


2 




ST2 


61-2 


10-i»-60 


P 


S 




3 

1 


3 


X-1 


3 




ST3 


61-3 


12-4-60 





F 


CO 


k 


h 


X-1 


4 




ST4 


61-4 


2-16-61 





S 


5 


5 


X-1 


5 




ST5 


61-5 


6-3O-6I 





F 


m 


5 


6 


X-1 


6 




ST6 


62-1 


8-25-61 





F 


^ 


7 


7 


X-1 


7 




ST7 


62-2 


10-19-61 


P 


S 




8 


8 


X-1A 


8 




ST8 


62-3 


3-1-62 


Re 


5 




9 


9 


X-2 


9 




ST9 


62-4 


3-29-62 


P 


S 




10 


S-1 


X-2 




1 


111 


62I5' 


4-26-62 





F 




n 




1* X-2M 




2 


112 


62-6 


5-24-62 





F 




12 




2* X-2M 




3 


117 


63-1 


8-23-62 





S 




13 


10 


X-3A 


10 




114 


63-2 


8-31-62 


Re 


F 




\h 


11 


X-3 


11 




115 


63-3 


12-16-62 





S 




15 


1 


X-3 




4 


118 


63-4 


12-18-62 





S 


-D 


16 




3* X-3M 




5 


126 


63-5 


2-19-63 





s 


i 


17 


2 


X-3 




6 


119 


63-6 


4-5-63 





F 


m 


18 




4* X-2M 




7 


121 


63-7 


4-26-63 





F 


_ 


19(AEC-1) ** 


X-3 


12 




116 


63-8 


5-22-63 


Re 


S 


^ 


20 


3 


X-3 




8 


120 


63-9 


6-15-63 





s 




21 




5 X-4 


13 




113 


63-10 


6-28-63 





s 




22 


12 


X-3A 


14 




110 


64-1 


7-20-63 


Re 


F 




23 




6 X-2B 




9 


132 


64-2 


9-27-63 





F 




24 


13 


"•iX" 




10 


I22R 


""64ir' 


12-19-63 





S 




25 


14 


X-3 


15 




127R 


64-4 


3-27-64 





S 




26 


4 


X-4 




11 


I25R 


64-5 


6-3-64 





S 




27 




7 X-4 




12 


128R 


64-6 


6-25-64 





F 




28 


15 


X-4 


16 




I24R 


65-1 


7-20-64 


P 


s 




29 


16 


X-4A 


17 




129R 


65-2 


8-18-64 


Re 


s 


TJ 


30 


17 


X-4 




13 


134R 


65-3 


8-25-64 





s 


> 


31(AEC-2) 


X-3C 


18 




130R 


65-4 


10-9-64 


Re 


s 


m 


32 


1U 


X-4 




14 


123RR 


65-5 


1 0-9-64 





s 


_ 


33 


19 


X-4 


19 




133R 


65-6 


11-6-64 





s 


~~ 


34 


20 


X-4 




15 


135R 


65-7 


11-21-64 





s 




35 


21 (SM) 


X-4 


20 




137R 


65-8 


12-15-64 





s 




36 


22 


X-4 


21 




136R 


65-9 


4-29-65 





s 




37(A) 


23 (EV) 


B 


22 




I31R 


66-1 


8-10-65 





s 





CODE: *Not NASA procured. 

**AEC purchased from the Navy. 
A - Army payload on NASA vehicle. 
AEC - Atomic Energy Commission. 
AF - Air Force. 
EV - Evaluation vehicle. 
F - Failure. 
- Orbii. 



P - Probes. 

R - Recert if icat ion. 

Re - Reentry. 

RR - Double recert if icat ion. 

S - Success. 

SM - San Marco. 

ST - Development vehicles. 



OF POOR QUALIIY 



k38 



TABLE CLI I I (b) - SUMMARY OF RESULTS (Phases IV and V) 



PAYLOADS (2't) (lO) (6) 



TOTAL 
LAUNCHES 

38 
39(FR) 

kO 
k] 
k2 
^3 
kk 
hS 
kS 

^7 
k8 

^3 
50 
51 
52 
53 
5it 
55 
56 
57 
58 
59 
60 
62 
73 



LAUNCH SITE VEH. 
NASA NAVY AF CONF. WALLOPS WTR NO. 



LAUNCH 



2k 
25 

26 



10 



27(SM) 
28 



29 



30 



31 
33 
^3 



II 



12 



13 



9 
10 

11 
12 



13 



X-4 
X-it 

A 

A 
X-4A 

A 

B 

A 

B 

B 

A 

B 

B 

A 

B 

A 

A 

B 

A 

8 

B 

A 

B 

B 

B 



23 



2k 



16 
17 
18 

19 
20 
21 



25 



26 



27 
32 



22 
23 
2k 
25 
26 
Af rica-1 
27 
28 
29 
30 

31 
32 

33 



138R 
139R 
140C 
l't2C 
litlC 
143C 
145C 
l't6C 
l't7C 
lUSC 
I49C 
150C 
151C 
IS'tC 
153C 
155C 
156C 
152C 
157C 
159C 
158C 
162C 
160C 
161C 
l^itCR 



FY 

66-2 

66-3 

66-4 

66-5 

66-6 

66-7 

66-8 

66-9 

66-10 

67-1 

67-2 

67-3 

67-4 

67-5 

67-6 

67-7 

67-8 

67-9 
68-1 
68-2 
68-3 
68-4 
68-5 
68-7 
71-6 



DATE 

11-18-65 

1 2-06-65 

12-21-65 

1-28-66 

2-09-66 

3-25-66 

4-22-66 

5-18-66 

6-09-66 

8-04-66 

8-17-66 

10-28-66 

1-31-67 

4-13-67 

4-26-67 

5-05-67 

5-18-67 

5-29-67 

9-25-67 

10-19-67 

12-04-67 

3-01-68 

3-05-68 

5-16-68 

6-20-71 



TYPE RESULT 











Re 





























Re 









Re 



S 
S 
S 
S 

s 
s 
s 
s 
s 
s 
s 
s 

F 
S 

s 
s 
s 

F 
S 
S 
S 
S 
S 

s 
s 



61 
63 
64 

65 
66(ESR0) 

67 
68 
69 
70 
71 
72 
74 
76 
77 
81 



32 
34 
35 
36 
37 
38 



14 



39 

40 

41 

42 (SM) 

44 

46 

47 

50 



-5C 
B 
B 
6 
B 
B 
A 
B 
B 
B 
B 
B 
B 
B 
D 



28 
29 



30 
31 



34 

35 
36 
37 
38 



33 
35 



Africa-2 
Africa-3 



Afrlca-4 
Afrioa-5 



164C 

165C 

168C 

I67C 

172C 

169C 

176c 

I71C 

174C 

175C 

173C 

177C 

166C 

163CR 

170CR 



68-6 
69-1 
69-2 
69-3 
70-1 
70-2 
71-1 
71-2 
71-3 
71-4 
71-5 
72-r 

72-3 
72-4 

73-3 



4-27-68 

8-08-68 

8-22-68 

10-03-68 

10-01-69 

11-07-69 

8-27-70 

9-30-70 

11-09-70 

12-12-70 

4-24-71 

7-08-71 

9-20-71 

11-15-71 

11-16-72 



Re 



Re 









Re 









P 







S 
S 
S 
S 
S 
S 
S 

s 
s 
s 
s 
s 
s 
s 
s 



-u 
> 

to 



CODE: A - Configuration A 
AF - Air Force 
B - Configuration B 
C - Certified 
D - Configuration D 
F - Failure 



FR - French 

FY - Fiscal Year 

- Orbit 

P - Probe 

R - Recertif ication 



Re - Reentry 

S - Success 
SM - San Marco 

X - Configuration X 



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LAUNCH DATA 



TABLE CLV1 - POSTFLIGHT SUMMARY, SCOUT S-178C 



SCOUT LAUNCH NO 



LAUNCH TIME <LOCALl 

1637 PST 



LAUNCH DATE 

29 October 1973 



LAUNCH S TE 



SLC;-5 VAFB, California 



PAYLOAD TYPE 



N-15 



PAYLOAD WEIGHT 



130.78 



m;ss:on type 
1973 - O8IA 



SCOUT MISSION 
TYPE NO 



66 



SUCCESS RA TO- 



58/61 » 0.951 



COUNTDOWN 








LAUNCH AZIMUTH (TRUE'. DEC 
182.0 


LAUNCH ELEVATION. DEG 
90.0 


W:ND Dl RECTON DEG 

001+ 


WND SPEED. KNOTS 
k 


RELATIVE HUMIDITY. % 
63 


VISIBILITY. STATUTE MILES 

20 


TEMPERATURE. 'F 
63.5 


B A ROME TER,"H G 

29.560 


Count was "begun at O908 Hours and proceeded normally until lift-off with no 
holds encountered. 



CONFIGURATION 












HEA T SHIELD 

3V-25, A- 50 


SPIN MOTORS 

(k) l.OKSl+0 


"E" SECTION T M 

No 


FIRST-STAGE MOTOR 

ALGOL IXC 
S/N 86 


SECOND-STAGE MOTOR 

castor iia 
s/n 191+ 


THIRD-STAGE MOTOR 

ANTARES IIA 

s/n HiB-310 


FOURTH-STAGE MOTOR 

ALTAIR II 

s/n ABL-150 


INSTRUMENTATION 

This was first Scout to utilize S-Band telemetry. There were five additional 
temperature sensors in the "D"-section Telemetry. 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


H2O2 ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


621.9 


622.9 


+1.0 


2NO STAGE 
183.0 


3RD STAGE 
19.2 


PERIGEE, N. Ml. 


580.0 


W9.9 


-90.1 


HjOj CONSUMED, LBS 


INCLINATION. DEG 


90.02 


90.2 


40.18 


2NO-STAGE BOOST 
J+2.5 


3RD-STAGE BOOST 
1.7 


MAXIMUM VELOCITY 
FPS 


2392U.7 


2370i+.5 


-220.2 


2ND-STAGE COAST 
6.3 


3RD-STAGE COAST 
2.7 


ALTITUDE. N. Ml. 


601+.1+ 


618.9 


+IU.5 




RETRO 

13.8 


SPIN RATE 

AT SEPARATION 

RPM 


161.3 


166.7 


+5.14- ( 3.3 i) 


SPIN BEARING TORQUE, IN-LBS 


TELEMETRY COVERAGE 

Vandenberg AFB and San Nicolas Island provided telemetry coverage with both 
receiving through third-stage separation from fourth-stage/payload. 



REMARKS AND/OR ANOMALIES 



1. A voltage bias was observed on the telemetered small pitch motor matrix. 

2. A similar voltage bias occxirred on the upper roll motor matrix. 

3. The middle "D" section spin appeared to have terminated at separation 
of the third- stage from the fourth- stage. 



8^ 



CUMENTATION 



NASA PREFLIGHT PLANNING REPORT 

AF FLIGHT TEST PLAN LTV-VSD-T Report 



3-3'+100/lR-l dated 11 January 1971 
Revision C dated 1 October 1973 



TRANSMITTAL LETTER 



3-56OOO/LAVO-8 dtd 15 January 1971 
2M-l6000/3L-i+033 dtd 3 October 1973 



FINAL FLIGHT REPORT 



■RANSMITTAL LETTER 



LTV-VSD-T Report 2-l60O0/l+R-l4- dated 

18 February, 197^4- , Addendum A dtd 22 
March IQlfh 

WCUI^I rcil^^pee B>.*-i.M..>.<.r. i->i-««E-i-i-rii-i^. _,.»., 



2M-I6OOO/UL-325O dtd 20 February 197^ 
2M-l6000/i+L-3U23 dtd 27 March 197^ 



VEHICLE SUCCESS RATIO SINCE R EC E R T 1 F I C A T ION 



450 



LAUNCH DATA 



ORIGir^AL PAG2 IS 
OF POOR QUALin^ 

TABLE CLVIl - POSTFLIGHT SUMMARY, SCOUT S-179C 



SCOUT LAUNCH NO 

94 



LAUNCH TIME (LOCAL! 

0042 PDT 



PAVLOAD TYPE 

P76-5 



LAUNCH DATE 

22 May 1976 



PAYLOAD WEIGHT 
LBS 



151.64 



M;SS:ON TYPE 

1976-047A 



LAUNCH S TE 



SCOUT MISSION 
TYPE NO. 



SLC-5, VAFB, California 



76 



SUCCESS RAT.O- 

67/71 = 0.9437 



COUNTDOWN 



LAUNCH AZIMUTH ITRUE!. DEC 

193.828 



RELATIVE HUMIDITY % 

86 

REMARKS 



LAUNCH ELEVATION. DEC 

90.0 



VISIBILITY. STATUTE MILES 

7 



rND DIRECTON DEG 

064 



TEMPERATURE. 'E 

53 



W NO SPEED KNOTS 

4 



BAROMETER,"HG 

29.693 



T-0 was delayed approximately two minutes due to a train in the area. 



CONFIGURATION 



HEAT SHIELD 

34/-40.S/NA-409 

Plhst-STAGE MOTOR 

ALGOL lie 
S/N 83 



SPIN MOTORS 



(4) 1.0KS40 



SECOND-STAGE MOTOR 

CASTOR IIA 



S/N 193 



THIRD-STAGE MOTOR 

ANTARES IIA 
S/N HIB-402 



4TH-STAGE T/M 

Yes 



FOURTH-STAGE MOTOR 

ALTAIR IITA 
S/N E-21 



INSTRUMENTATION 

Eight temperature measurements and one vibration measurement were added 
to "D"-section T/M. 



PERFORMANCE 












PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


H2O2 ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


633.75 


577.09 


-56.66 


2ND STAGE 

184.0 


3RD STAGE 

18.1 


PERIGEE, N. Ml. 


540.99 


536.42 


- 4.57 


H2O2 CONSUMED, LBS 


INCLINATION. DEG 


99.88 


99.67 


- 0.21 


2ND-STAGE BOOST 

26.0 


3.0 


MAXIMUM VELOCITY 
EPS 


24248.7 


24183.2 


-65.5 


2ND-STAGE COAST 

11.5 


1.3 


ALTITUDE. N. Ml. 


541.19 


536.99 


- 4,20 




RETRO 

12.8 


SPIN RA TE 

AT SEPARATION 


152.4 


161.2 


+ 8.8 ( 5.8^) 


SPIN BEARING TORQUE. IN-LBS 

54,7 


TELEMETRY COVER 

VAKB (TRS) had 
Pt. Mup.u from T 
except for 30 s 


GE 

good "D"-se( 

+ 22 to T H 

ec at 3rd-s1 


:tion T/M to 743 
h 750 seconds. 
:age Ignition an 


sec except for 30 sec at 3rd-stage Ipnition and 
^.'ATB (TRS) had good 4th-stage T/M from T-0 to T + 8A3 
d Pt. Miigu from T -1- 9 to T + 842 seconds. 



REMARKS AND/OR ANOMALIES 



A lower injection altitude was caused by the effects of lower than predicted altitude, velocity 
and path angle at 3rd-stage burnout, propagated through the long (about 535 sec) 3rd-stage coast 
phase About 27Z of the injection velocity deviation resulted from lower stage performance; 
the remaining 732 was caused by lower 4th-stage motor performance. The deviations in injection 
path angle and azimuth are attributed to pitch-up and yaw-left tip-off disturbances at fourth- 
stage ignition. 



DOCUMENTATION 



NASA PRE-FLIGHT PLANNING BROCHURE 
AF FLIGHT TEST PLAN 

Vought Corp. Report No. 2-16000/6R-9 
dtd 6 April 1976 



FINAL FLIGHT REPORT 



Vought Corp. Report No. 2-16000/6R-24 
dtd 21 September 1976 



TRANSMITTAL LETTER 



2M-16000/6L-3388 dtd 12 April 1976 



TRANSMtTTAL LETTER 



2M-16000/6L-4050 dtd 24 September 

1976 



VEHICLE SUCCESS RATIO SINCE REC E R T I Fl C A TION 



^ QRIGINAl PAGE iS 

OF POOR QUALITY 

LAUNCH DA TA^^^*-^ *^'-^"' " POSTFLIGHT SUMMARY. SCOUT S-I8OC 



SCOUT LAUi'lCH NO. 

75 



P»YLO*D TYPE 

CAS-A 



LAUNCH TIME ILOCALl 

l'+39 EDT 



1>AY LOAD WEI GHT 

^"^ 179.30 



LAUNCH DA TE 

16 Au^ 19Y1 



M.SSION TYPE 
I97I-7IA 



COUNTDOWN 

NCH A2 :m 

126. If? 



Wallops Island. Va. 



SCOUT MISSION 
TYPE NO 



50 



SUCCESS RATIO- 

W52=0.9^2 



LAUNCH AZIMUTH (TRUE!. DEg" 

I 



RELATIVE HUMIDITY 

75 

f<e:marks 



LAUNCH ELEVATION DEG 

89.91 



VISIBILITY. STATUTE M.LtT 
It 



Y.'iND DIRECT-ON DEG 



T EMPERA TUHE, 'F 

77 



w:nd speed, knots" 

13 



BAROMETER,"HC 
30.100 



12 ^^uST^"^,.^^ 

spectiveOy, the countdSvn proceed^ noJSIllJ^^ ^°'' ""^"^^ ^^^^^^^ ^e- ^ 



CONFIGURATION 



^L*/0C:"^'-g/M A /-JsPi' N MOTORS ^ — ____ 

W-25^_SAA-6d (2) 1.0 KS IK) (2) 1.0 KS 75 



"^S l-STAGE MOTOR 

Algol lie, S/N 78 



INSTRUMEN TATION 



.tCONO-S TAGE MOTOR 

Castor IIA, S/n 



JhTrd^TtXgTTJotor" 

IC259-B3,Antares II 
S/N HIB-314 



'•E"iECTION T 

les 



^x^:^;d^.^^^^!^ki^^=^^n 



FOURTH-SIAGE MOTOR 

FW-te, Altair III 

s/n 2223-15 



T/M instrumentation ut?I?:S. Fi?sf vSiSf 1S?^^???^ 



PERFORMANCE 



PARAMETER 



APOGEE. N. Ml. 



pe:rigce,n. mi. 



PREDICTED 



ACTUAL 



^^85. 88 493.33 



inclination, DEG 



MAXIMUM VELOCITY 
FPS 



ALTITUDE. N. Ml. 



SPIN RATE 

AT SEPARATION 

RPM 



^83.36 369.80 -113.56 



50.00 50.16 



DEVIATION 

FROM 

PREDICTED 



+7.45 



+0.16 



HjOj ON BOARD 

AT LIFT OFF 

LBS 



^"185^.5 



>^:^S^GE 



H2O2 CONSUMED, LBS 



2ND STAGE BOOST 

26*4 



||2ND STAGE COAST 
11.1 



^, 7:^ 1 180-0 ^.20 (■H),ii?^)f^'^66:6i; 



3RD STAGt BOOST 

2.9 



3RD STAGE COAST 

2.6 



RETIVJ 

12^ 



SPIN BLARING TORQUE, IN-LBS 



T/M"coverage -f^c^ii-ilug^ to^Oo! lecS^f rKg^^f j^r%"?'°^li? |^/V: ^^°-^^°" 
provided good combined "E" section T/McoveJfJp r^m'ir, 'h ^"^.^"^^eua stations 
Normal loss of signal during SndT/^^f^L^^^Jrfi^n' l"? "^'^ ^^=°"^^- 




cfuiiHg-^hl^g:up\"^fii^s'?S^^a^?^^S24efS'S5l?e^^^ 

stage coast - caused by cracking nozzle coSe Sit !w ^^^ during tth- 

'• ^LTto'l^TJ%flt^,_^f''''' ^^-^ P-ided'combined coverage f\o. 



DO CUMENTAT ION 



JnaSA PHt.l LIGHT PLANNING RtPORT 
Jaf flight TEST PLAN 



LTV RPT. 3-3^100/lB-42, DTD 15 June 19 
W/Rev A DTD. 28 July I971 



'-m^m: "%^4iOO/2R-13, DTD lO Mar 19 
W/Rev A Dated 18 May I972 



vehicle success RATIO S.NCE F.Ic E R T . F i C A"'fTH;r 



TRANSMITTAL LETTER 




,^ LTV LTRS 3-3^100/11-3626 and - 3799 

dated 2LJune I971 and 29 July 1971 
EfiapfiCtiyfiJjili ' 

^2'-'-^liW^^-5'i34l00/2L-3300 and -3508 
dated I7 March I972 and 29 Ufay 
1972, respectively. 



452 



ORIGINAL PAGE 13 
OF POOR QUALITY 



TABLE CLIX - POSTFLIGHT SUMMARY, SCOUT S-I8IC 



LAUNCH DATA 


















SCOUT uaunC^NS. 

83 


LAUNCH T!ME (UOCAU) 

O32U PST 


UAUNCH DATE LAUNCH STE 

16 December 1972 SLC-5, SVAFB. Calif. 


S 


PAYI.OAD TYPE 

AEROS 


PAYLOAD WEIGHT 
"■"' 279.72 


M;SS:ON TYPE 

1972-lOOA 


SCOUT MISSION 
TYPE NO g^ 


SUCCESS rat;o- 
57/60 = 0.950 



COUMTDOWN 



LAUn£kI Aziluiut^ (TRUE;, dec 
190.82 



RELATIVE HUMIDITY. % 
65 



LAUNCH ELEVAT!ON. DEG 
90.00 



VISIBILITY, STATUTE MILES 

10 



w:nd direct'on deg 
110 



EMPERATURE. *F 
51 



NO SPEED. KNOTS 

9 



BAROMETER,"HG 
29.B5I 



Countdown vm l)egua at 2085 W. 15 Deco*or, awl proceeded to launch tlae with three holda encountered. 
The first hold (10 alnntea) «m due to a weak algnal at the teleaetry ground atatlooi the eecood (20 alnntea), 
to clear the pad of noa-essentlal paraoanel; and the third, at the cooclualon of Tkak 6 until the scheduled 
■tart of Basl r "^ "<n^ -<-1'" rnrrectla. of M>.19 d««ree In l«llich atllth. 



CONFICURATIOM 



HEAT SHIELD 

U2/-U5,S/N A-50l| 

ALGOL III 
S/N 5502-U 



sPTTTMcrraUT" 

(U) 1.0 KS 75 



ttlONO-ifAOk MOTOR 



THiRD-sYAiE m6t6r 
X259-B3, ANTARES II 



:astor iia, s/n 191 s/n hib-sis 



4TH-STAOC MOOUI.E T/M 

Yes 



FOURTH>STACE MOTOR 

FW-US ALTAIR III 
S/N 2376-2 



INSTRUMENTATION 

Standard "D' aectlon T/N InatroMatatloo i n o l u aed a $0 "g' peak-to-peak AiGOL III rlbnaeter ayataa 
and ten additional taaperatnre aenaors.roorth-atage T/N ayataa waa the third S-hand T/N ajrataa to he 
used, and inelaaad Inatnintatloo of the B^rload Beparatlcn Tlaer Start Switch Tnparatnra. hgrloaS 
aeparatlco waa alao recorded by fourth-atage T/M ayatea. 



PERFORMANCE 












PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 
PREDICTED 


H2O2 ON BOARD 

AT LIFTOFF 

LBS 


APOGEE. N. Ml. 


1+33.9 


U7U,2 


+U0.3 


2ND STAGE 
I8U.O 


SRO STAGE 
19. 1» 


PERICEEjN. Ml. 


1PQ.1 


12U.1 


-5.0 


H2O2 CONSUMED. LBS 


INCLINATION, oca 


97.2 


96.9 


-0.3 


2ND-STAGE BOOST 

Ui.o 


IRO-STA6E BOOST 

U.9 


MAXIMUM VELOCITY 

rps 






_ 


2ND-STAGE COAST 

36.6 


SRD-STACE COAST 

0.6 


ALTITUDE, N. Ml. 




„ 


„ 




RETRO 

12.9 


SPIN RATE 

AT SEPARATION 

RPM 


lk6.h 


11+2.1 


-1|.3 (-2.9^) 


SPIN BEARING TORQUE, IN-LBS 
5U.3 


TtLEtU^tHV c6vttRAgE ■ ^. 
V«n(1ie), the prlMry aonrce of T/M data, prorlded good data to ^31 aecoods fll^t tlM for "V 
■eetlOQ and to li6l aacooda flltfit tlM for fourth-stage aodule. Ft. Nugu "D" aeetloo and fourth- 
stage aodnle telaaatry data guaUty waa good frc« 9 to 37»» aacooda fllrfit tlae and frai 19 to 
itOO aeeonda fll^t tlae, respectively. Aircraft telaMtry coverage, uaad to detezalne fourth-stage 
separation frM payload, was ae«alred at 3l»7 seconds and was good during the perloda 360 to $00 
seconds. 5;6 to 6l2 aecoods. and 6$9 to 710 aecoods fll^t tlM. 



REMARKS AND/OR ANOMALIES 



nie differences between 1 naiisiiiliiil and actual fin deflections are attributed to anoaalles In the pitch 
rate gain and the teleaetered yaw dlsplaceaent gyro output. The Investigation of theae anoaalles will 
appear as an addendua to the Post Fll^^t Report for this vehicle. 



DOCUMENTATION 

X | NASA PREFLIGHT PLANNING REPORT 
__JAr FLIGHT TEST PLAN 

LTV Report 3-3ltl00/2R-6l dated 
13 Nov 1972 



TRANSMITTAL LETTER 

3-3U100/2L-U205 dated ik Nov 1972 
?- 56100/ 3AV0^176 dated lU Nov 1972 



FINAL FLIGHT REPORT 



TRANSMITTAL LETTER 



LTV Report 2-l6000/3R-27 , dated 
13 June 1972 

• VEHICLE SUCCESS RATIO SINCE RECKRTI FIC A TION 



2-16000/ 3I,-37U0 dated I8 June 1973 
2-56IOO/3AVO-I35 dated I8 June 1973 



OF POOR QUALITY 



453 



LAUNCH DATA 

SCOUT LAUNCH NO 



TABLE CLX - POSTFLIGHT SUMMARY, SCOUT S-182C 



80 



PA YLOAO TYPE 

INS-l(RTG) 



LAUNCH TIME (LOCALl 

1050 PDT 



PAYl_OAD WEIGHT 

"" 206.1tlt 



LAUNCH DA TE 

2 September 1972 



«.SS:ON TYPE 

1972 - 69A 



LAUNCH S'TE 

SLC-5, SVAFB, Calif. 



SCOUT MISSION 
TYPE NO /Tp 



SUCCESS PATO' 

5V57 = 0.9»+7 



COUNTDOWN 

LAUNCH AZIMUTH (TRUE!. DEC 



182.028 



RELATIVE HUMIDITY 

neuARKS 



LAUNCH ELEVATION. DEC 

90.00 



VISIBILITY. STATUTE MILES 
1 



WND DIRECT ON OEG 
258 



TEMPERATURE. 'F 

68 



W ND SPEED KNOTS 

5 



BAROMETER,"MG 
29.550 



Countdown uas begun at 0320 PDT, 2 September, and except for an eleven-minute hold to avalt Range support 
and a seven-minute hold to let telemetry van recover telemetry signal, proceeded normally. No wind aiming 
correction required since vehicle was equipped with Roll-Taw Compensation Unit. 



CONFIGURATION 



4EAT SHIELD 



3U/-li0,A-l+0U 



SPIN MOTORS 



FIRST-STAee mot6r 

ALGOL IIC,S/N 8I| 



INST rumen TATION 



(2) 0.6 KS kO (2) 1.0 KS 75 



second-stase motor 

CASTOR IIA 

S/N 197 



THIRD-STAGE MOTOR 

X259-B3,AM'ARES II 
S/N HIB-311 



4TH-STAGE MODULE T/M 

No 



FOURTH-STAGE MOTOR 

FW-US, ALTAIR III 
S/N 2376-1 



standard "D" section T/n Instruaentation. Second vehicle to incorporate a roU-yaw ec^enaatlco 
device in the guidance ayatem. 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjO} ON BOARD 

AT LIFT OFF 

LBS 


APOGEE, N. Ml. 


^9h.3h 


it57.58 


-36.96 


2ND STAGE 
180.0 


3RD STAGE 

18.8 


PERIGEE,N. Ml. 


U9.9I 


U05.32 


-I+I+.59 


H2O2 CONSUMED. LBS 


INCLINATION. DEC 


90.0 


90.1 


+0.1 


2ND-STACE BOOST 

38.6 


3RD-STA6E BOOST 
2.16 


MAXIMUM VELOCITY 
FPS 








ZND-STAGE COAST 

5.2 


3RO.STACC COAST 

2.6U 


ALTITUDE. N. Ml. 


— 


- 


_ 




RETRO 

12.9 


SPIN RATE 

AT SEPARATION 

RPM 


167.8 


169. It 


+1.6 ^0.9 ^^ 


SPIN BEARING TORQUE, IN-L8S 

62. u 


TeLEMETRY COVERAGE — 

Scout S-iaSG waa not equipped with t fourth-stage module T/N ayatem. Oood quality "D" Mction 
telaaatry data ««• received by VAn(TRS), with the exception of dropout during moat of thlrd-atact 
bum period; data recovery waa good from then until loss of aiffial at about 838 aeeooda fllgbt tiaa. 



REMARKS AND/OR ANOMALIES 



1. Around 48 aeconds flight time the pressure transducer signal changed alope and began to lag the 
. deereaalng presaure. At 49.3$ seconds fli^t time the signal abrupty dropped about 25 paia to a level 

in line with the slope prior to 48 aeconds and followed the original slope, ma ancamly is attributed 
to a temporary ali^t increase of friction within the transducer. 

2. Daring third-stage coast the pulae aaplitude of segMnts 3, I3, and 23 of the 52.5kHz telemetry 
channel deoreaaed to a level lower than the proper level. Thla condition laated for 0.8 second, and 
was subsequently attributed to the presence of motor exhaust gases at J69 and J70 (heatahield jumper connector; 

3. Vehicle's heatahield was modified to provide additional cooling for the UB-l Spacecraft 
due to the Radioisotope '^«fasl usncrstcr. _. — . / 



L- ^ 



)OCUMENTATION 



m 



ASA PREFLIGHT PLANNING REPORT 



AF FLIGHT TEST PLAN 



VMSC-T Rept 3-3'+100/2R-39 dated 
7/20/72, Rev. A dated 8/7/72 



FINAL FLIGHT REPORT 



LTV Rept 2-I60OO/3R-8 dated 23 Feb 197! i 
Rev. A dated 25 April 1973 



TRANSMITTAL LETTE^^j. 

3-56006/2AVO-88 dated 2k July 1972 
3-3|il00/2I«-3732 dated 2 U, July 1972 



3-5p000/2AV0-115 dated ik Aug 1972 



2-56100/3AV0-47 dated 7 Mar 1973 
2-I60OO/3L-31I+7 dated 8 Mar 1973 
2-5§100/3AV0-93 dated 25 April 197' 
2-lb000/3L-3373 dated 30 April 197' 



. VEHICLE SUCCESS RATIO SINCE RECERTIFIC A TION 



454 



ORIG'.ri«^l PAQS IS 
OF POOR QUALITY 



LAUNCH DATA 



TABLE CLXI - POSTFLIGHT SUMMARY, SCOUT S-183C 



SCOUT LAUNCH NO. 



73 



LAUNCH TIME (I.OCAI.I 



121^7 PST 



LAUNCH DATE 

11 December 197 



Y^^. 



, SVAFB, Calif 



PA YLOAD TYPE 

UK-4 



:vs^°^s^W"wn-i6§A 



SCOOT MlSSlQtV, 
TYPE NO DU 



^""52/^'°- .945 



COUNTDOWN 



LAUNCH AZIMUTH (TRUC:. OEG 



173.35 



LAUNCH ELEVATION. DEC 



W!ND DIRECTION DEG 



90.00 



290 



w:nd speed, knots 

12 



RELATIVE HUMIDITY. % 



VIS:B1LITY. STATUTE MiLES 



TEMPERATURE. 'F 



69 



15 



52 



'*^.^55-" 



REMARKS 



CumiLQuwn Sta rt ea at 05^5 FJJl ' , ll December, and proceeded normally 



Wind aiming correction of ■K).28-deg in latinch azimuth. First vehicle launched 
from VAFB by VMSC-T field crew personnel. 



CONFIGURATION 



HEAT SHIELD 



3V-25, s/N A-6; 



SPIN MOTORS 



(2) 1.0 KS 40 (2) 1.0 KS 75 



■E" SEC TION T M 

No 



FIRST-STAGE MOTOR 

Algol lie, S/N 89 



SECOND-STAGE MOTOR 

Castor IXA, 
R/n 1,9? 



HIR[>STA.(jE MOTOR 

X259-B3,Antares II 

s/n HiB-302 



FOURTH-STAGE MOTOR 

FW-te, Altair III 

s/n 2223-12 



INST RUMEN TATION 



Standard S-Band "D" section T/M instrumentation utilized. First 
Scout vehicle flown from VAFB with S-Band T/m. 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjOj ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. • 


299.7 


323.6 


+23.9 


r N D STAGE 

180. 


jRD STAGE 
19.0 


PERIGEE, N. Ml. 


297.0 


261.7 


-35.3 


H2O2 CONSUMED, LBS 


INCLINATION, DEG 


83.0 


83.0 





2ND STAGE DOOST 
39.9 


3RD STAGE BOOST 
l+.l 


MAXIMUM VELOCITY 
FPS 








2ND STAGE COAST 

39.3 


3RD STAGE COAST 

1.7 


ALTITUDE, N. Ml. 










RETRO 

13.2 


spin RATE 

AT SCPARAT ION 

RPM 


151+.G 


156.3 


+1.5 (■K).97^) 


SPIN BEARING TORQUE. :N-LBS 
U7.8 


TELEMETRY COVERAGE ^^,^j„^^pg^jj^^x pj^,gjjj J ^^ downrangc Aircraft receivin ; 
stations provided satisfactory combined T/M coverage from laxaich through 599 
seconds flight time. Nominal amount of signal dropouts experienced during 
flight coverage. 



SEM A R KS AND OR ANOM AL IES „___, ,__^ 

.. All vehicle sytftams perrormea normally^ command Destruct Receiver signal 
strength was erratic when vehicle was under control of SNI AN/FBW-2 trans- 
mitter from 80 to 297 and ^7 to 593 seconds flight time. 
2. VAFB and SNI AN/FPS-16 radai» provided satisfactory combined tracking 
coverage from 5 to 699 seconds flight time. 



8Sfe 



UMENTATION 



MASA ^'RK^LIC.HT PLANNING RCPOF^T 



AF FLIGHT TEST PL*N 

noVRPT 3-3410O/IR-73, Dated 

5 Nov 1971 w/Pagel-1 Rev. 11 Nov 197I 



^ LIRS 3-3&100/1L-4221 and-i>252, KCD 
5 November I971 and 12 November 1971 
respectively. 



FINAL FLIGHT REPORT 



LTVRpD 3-341OO/2R-3I, Dtd 31 May 197J 
W/Rev A dated 20 October 1972 



TRANSMITTAL LETTER 



LTV LTRS 3-34IOO/2L-3543 & -4ll4, KED 
1 Jvine 1972 & 26 Oct. 1972, re 



specti' rely 



VEHICLE SUCCESS RATIO SINCE R E C t R T 1 F I C A T I ON 



k55 



ORIGJNAL PAG«- fs 
OF POOR QUALITY 



TABLE CLXM 



LAUNCH DATA 



POSTFLIGHT SUMMARY, SCOUT S-l8^C 



SCOUT LAUNCH NO 

79 



LAUNCH T;Me ILOCALI 



1110 EDT 



LAUNCH DA TE 



13 August 1972 



LAUNCH s TE Mark II Launcher 
Wallops Island, Va. 



PA VLOAD TYPE 



MTS-A 



PAY LOAD WEIGHT 



i;SS:ON TYPE 

iqT2 - 6lA 



SCOUT MISSION 
TYPE NO , 

61 



SUCCESS RA TO' 



COUNTDOWN 








LAUNCH AZIMUTH (TRUEl. DEG 

90.17 


LAUNCH ELEVATION. DEG 
89.98 


WND DIRECTON DEG 
170 


WND SPEED. KNOTS 

8 


RELATIVE HUMIDITY -. 

79 


VISIBILITY. STATUTE MILES 

7 


TEMPERA TU RE. 'F 

76 


BA ROME TER,"H G 

30.11 


Countdovn was begun at O3U3 EOT, 13 August, and except for a brief hold to allov the Range Firing Console 
Operator to review the permissive relay RlOO circuit, proceeded normally. Azimuth correction due to winds 
not necessary. 



CONFIGURATION 



HEAT SHIELD 

3J+/-i+0,S/N Ai+02 



PIRst-STAOE MOTOR 

ALGOL III 
S/N 5502-2 



SPIN MOTORS 



(it) 1.0 KS 75 



SECOND-STAGE MOTOR 

CASTOR IIA,S/N I87 



^^'§5"-B3°^N^A?iES II 
S/N HIB-303 



4TH STAGE MODULE T/M 

Yes 



FOURTH-STAGE MOTOR 

FW-ltS, ALTAIR III 
S/N 2376-8 



INSTRUMENTATION Standard D" section T/M Instnaentation systea. 7ir8t Scout to fly with an ALQOL III first-stage 
motor and the first to fly with tour 1.0X875 spin motors to spin-stabilise the payUad and fourth- 
stage motor prior to third-stage separation. Also, the first Scout to be launched frcii Wallops 
Island with fourth-stage nodule telemetry. Special instrumentation, including thermistors and 
vibrometers. was installed to determine the effect of the AIGOL III motor on vehicle environment. 



PERFORMANCE 












PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjOj ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


it27.9 


hh3.9 


16.0 


2ND STAGE 
181.0 


3RD STAGE 

19.0 


PERI GEE, N. Ml. 


263.6 


269.3 


+ 5.7 


H2O2 CONSUMED. LBS 


INCLINATION. DEG 


37.7 


37-7 





2ND-STAGE BOOST 
51.0 


3RO-STAGE BOOST 

1*.2 


MAXIMUM VELOCITY 
FPS 


mm 


^_ 


nm 


2ND-STAGE COAST 

20.1 


3RD-STACE COAST 

1.5 


ALTITUDE. N. Ml. 


^ 


— 


M 




RETRO 

12.3 


SPIN RATE 

AT SEPARATION 

RPM 


166.6 


167.0 


+0.1|(+0.2 i) 


SPIN BEARING TORQUE. IN-LBS 

66.6 


TELEMETRY COVERAGE 

Performance data were recorded from "D" section and fourth-stage telemetry systems at Wallops Is., 
Bermuda Is., and Ascension Is. Ihls was the first use of S-band frequency telemetry for both systems. 
Coverage of both systems at Wallops Island was characterized by ninerous dropouts; however, slffial 
was not lost until about 620 seconds flight time for both systems. Fourth-stage module coverage by 
Benmiilii was good from shortly after acquisition (11$ seconds) until about 72U seconds fll^t time. 
Ascension Island acquired the fourth-stage mediae telemetiY at about 1279 seconds and coverage was 
generally intermittent throughout until about 1717 seconds flight time. 



REMARKS AND/OR ANOMALIES 



All vehicle systems performed as predicted with the single exception of a momentary malfunction of 
of the solid-state conamtator in the "D" section telemetry system. 



)OCUMENTATION 



ASA PREFLIGHT PLANNING REPORT 
AF FLIGHT TEST PLAN 

LTV Rept 3-3Ul00/2R-i+0 dated 7/21/72 
Rev A dated 8/7/72 



FINAL FLIGHT REPORT 

LTV Rept 3-3^100/2R-67 dated 12/22/72 
Rev A dated 13 April 1973 



TRANSMITTAL LETTET , 

3-5D000/2AV0-8Q dated 2^+ July 1Q72 

3_3kioo/2L-3729 dated 2l+ July 1972 
3-56000/2AV0-112 dated 8 Aug 1972 
?--^li1nn/PT.-3iQ7 Hb+pH R fliig 107? 






!-^St)607^Af 6-199 dated 22 Dec 1972 
3-3i+100/2L-U373 dated 22 Dec 1972 
3-56IOO/3AVO-89 dated I6 April 1973 
2-i6000/3L-33^5 dated 19 April 1973 



VEHICLE SUCCESS RATIO SINCE REC E R T I Fl C A T ION 



ORIGINAL PAGE IS 
^56 OF POOR QUALITY 

TABLE CLXm- POSTFLIGHT SUMMARY, SCOUT S-185C 



LAUNCH DATA 



SCOOT LAUNCH NOJUAUNCH T:ME (UOCALl 



82 



1617 PST 



PA YI.OAO TYPE 

ESRO IV 



PAVLOAD WEIGHT 
•"^ 25U.IO 



LAUNCH OATE 

21 November 1972 



I.SSION TYPE 

1972 - 92A 



LAUNCH S TE 

SliC-^, SVAFB, Calif. 



SCOUT MISSION 
TYPE NO gj^ 



SUCCESS RAT.O* 



56/59 = 0.9>*9 



COUNTDOWN 



LAUNCH AZIMUTH ITRUE!. DEG 
183.131 



RELATIVE HUMIDITY % 

78 



LAUNCH ELEVATION. DEG 
90,00 



VISIBILITY, STATUTE MILES 

10 



W NO DIRECT ON DEG 
300 



TEMPERATURE. 'F 



.52_ 



WND SPEED. KNOTS 

7 



BAROMETER."HG 
29.770 



H«IJ 1 BU A 

Arst countdoHn was begun at O915 PST, 20 Novenber, with only a 21-mlnute hold to await Dange support. 
When Sequencer Step 13 did not respond, and when an attempt to co^und Fourtb-Btage Module T/M Internal 
Power was unsuccessful, the countdown was aborted. "Bie second countdown was begun at O917 P6T, 21 Roveaber. 
A l»3-mlnute hold to await Rantw support was the only hold encountered. launch proceeded nomally- 
Wind aiming correction of -tO. ST degree in launch azimuth. 



CONFIGURATION 



HEA T SHIELD 



SPIN MOTORS 

3lt/-tt0.S/N A-lt 03| (2) 1.0 KSj+0 

TIBsT-STAGE MOTOR 



(2) 1.0 KS 75 



ALGOL III,S/N5502-3 



SECOND-STAGE MOTOR 

CASTOR IIA,S/N I88 



THIRD-STAGE MOTOR 

X259-B3,AIITARES II 
S/N HIB-312 



4TM-STAGe I1NOOUI..C T/M 

Yes 



FOURTH-STAGE MOTOR 

FW-ltS,ALTAIR III 
S/N 2223-13 



INSTRUMENTATION ^ . . 

Standard "D" section T/M InstruBentatlon Included the 125 "g" AlfiOL HI vlbroiKter systea and ten 
teaperature sensors; incorporated in the fourth-stage aodule teleoetry systea were the FW-I»S lateral 
123 "s" vlbrcmeter and the TV-kS longitoUnal 125 "g" vibrcmeter. Pay load separation was to b« 
recorded on IMG Channel I3 of the fourth-stage aodule telemetry system. 



PERFORMANCE 












PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


H2O2 ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


593. S" 


639. U 


+1^5.9 


2ND STAGE 
182.5 


3RD STAGE 

19. u 


PERIGEE,N. Ml. 


151.3 


135.8 


-15.5 


H3O2 CONSUMED, LBS 


INCLINATION. DEG 


90.8 


91.1 


+0.3 


2ND-STAGE BOOST 

33.2 


3RO-STAGE BOOST 


MAXIMUM VELOCITY 
FPS 


- 


- 


- 


2NO-STAGE COAST 

30.1 


SRD-STAGE COAST 

0.7 


ALTITUDE. N. Ml. 


_ 


^, 


_ 




RETRO 

12.9 


SPIN RATE 

AT SEPARATION 

RPM 


lit5.5 


1U7.0 


+i.5(+i.o i) 


SPIN BEARING TORQUE. IN-LBS 

U8.2 


TELEMETRY COVERAGE 

VAFBIIBS), the primary source of telemetry data, had good coverage of "D" section teienetry froB prior 

to launch to UoB seconds fli^t time, and good coverage of fourth-stage nodule teleaetry fro« lift-off 

to U58 seconds flight time with two brief data losses during first-stage operation. Coverage of "D" 

section at San Nicholas Island was essentially good (excluding the periods fron 60 to 191 seconds and 

froB 1»32 to 1»52 seconds flight tine) frcn 13 to U92 seconds flight tine. SHI fourth-stage aodule T/M 

coverage was good from 11 to UlS seconds flight time. 



R EMARKS AND/OR ANOMALIES j— , 

1. tWyload separation eveat was io be recorded, neither VATO nor UBl ground station, however, received 
telemetry data up to the predicted time of payload separation event. Aircraft coverage of fourth-stage 
T/M data was not available. 

2. Around 356 seconds fUght time the pulse amplitude of sesaents 3, 13, and 23 of tha 52.5UZ telemetry 
channel decreased to a level lower than the proper level. "Biis condition lasted for O.7 second, and 

was attributed to the presence of motor exhaust gases at J69 and J70 (heatshield Jumper connectors). 

Further investl^tlon established that this anomaly has occurred on five of six vehicles launched 

after S-17ac. and would not affeo t vehicle performance. 



)OCUMENTATION 



X InASA PREFLIGHT planning REPORT 
AF FLIGHT TEST PLAN 

VMSC-T Report 3-3ltlOO/2R-56 dated 

^ 20 October 1972 



FINAL FLIGHT REPORT 



VSD Report 2-l60O0/3R-l^ dated 

30 November 1973 



TRANSMITTAL LETTER , „_, 

3-56OOO/2AVO-I62 dated 20 October 197J 
3-3UIOO/2L-U095 dated 20 October 197£ 



TRANSMITTAL LETTER 

2-56100/3AVO-62 dated 2 April 1973 
2-I6000/3L-326U dated 3 April 1973 



• VEHICLE SUCCESS RATIO SINCE REC E RTI Fl C A TION 



^57 



ORIGINAL PAGE IS 
OF POOR QUALITY 



TABLE CLXIV - POSTFLIGHT SUMMARY, SCOUT S-186C 



LAUNCH DATA 



SCOUT LAUNCH NO. 



88 



LAUNCH TIME (LOCAL) 

Qlf^l PPT 



PAVLOAO TYPE 

AER06-B 



PAY LOAD WEIGHT 
•-" 280.65 



LAUNCH DA TE 

16 July igT'^ 



MISSION TYPE 

1974 - O55A 



LAUNCH S TE 



SLg-5 VAFB, California 



SCOUT MISSION 
TYPE NO —^ 



SUCCESS RA T.O* 



62/65 » 0.95^ 



COUNTDOWN 








rTUNtH AZIMUTH ITRUEi. OEG 
190.31*+ 


LAUNCH ELEVAT.ON. DEG 
90.0 


W ND DIRECT ON DEC 

35 


WNO SPEED KNOTS 

3 


RELATIVE HUMIDITY % 

87 


VISIBILITY. STATUTE MILES 

7 


TEMPERATURE. 'F 

55 


BAROMETER,"HG 
29.556 


BEMiWKi 

The coiintdown proceeded normally \mtil T - 3 minutes at lAiich time there 
was a hold of k minutes due to a train on the range. 



CONFIGURATION 



HEAT SHIELD 



k2/-k'y,S/^ 507 



PiniT-stA(i^ MoV6h 

algol iiia 
s/n 5502-9 



SPIN MOTORS 



{k) 1.0KS75 



SECOND-STAGE MOTOR 

CASTOR IIA 



S/N 200 



THIRD-STAGE MOTOR 

ANTARES IIA 

s/n HiB-315 



4TH-STAGE MODULE 

T/M Yes 



FOURTH-STAGE MOTOR 

ALTAIR IIIA 



s/n 2376-6 



INST RUMEN TATION 

Second Scout to have "Add-On" PCM system in "D" -section; eight additional 
Base "A" temperature sensors in "D"- section. S-Band Hh-stage T/M system. 



PERFORMANCE 












PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjOj ON BOARD 

AT LIFTOFF 

LBS 


APOGEE. N. Ml. 


486.1 


474.9 


-11.2 


2ND STAGE 
181.0 


3RO STAGE 
19.2 


PERIGEE,N. Ml. 


i2k.2 


119.3 


-4.9 


HjOj CONSUMED, LBS 


INCLINATION, OEG 


96.8 


97.4 


40.64 


2NO-STACE BOOST 

29-5 


3RO>STACE BOOST 
3.6 


MAXIMUM VELOCITY 
FPS 


26088.6 


26092.5 


+3.9 


ZND-STAGE COAST 
28.5 


1RD-STA6E COAST 

0.4 


ALTITUDE. N. Ml. 


121^.2 


120.0 


-4.2 




RETRO 

14.2 


SPIN RATE 

AT SEPARATION 

RPM 


li+5-9 


145.2 


-0.7 ( 0.5^) 


SPIN BEARING TOROUE, IN-LBS 
52.0 


TELEMETRY COVERAGE 

VAFB (TRS) and San Nicolas Island received and recorded telemetry data xmtil 
after fourth- stage separation. AN/FPS-16 radar data were acquired at VAFB 
(Site 2) from T + 2.87 to T + '+'*3-07 seconds flight time. 



REMARKS AND/OR ANOMALIES 



All systems performed as expected with no major anomalies. The two Base A 
Barrier Temperatxire sensors failed at 42 and 43 seconds flight time, respect' 
ively. All other temperature sensors functioned as expected. 



aOCUMENTATION 

A |NASA PREFLIGHT PLANNIN 



E 



G REPORT 



TRANSMITTAL LETTER 



AF FLIGHT TEST PLAN 



LTV-VSD-T Report 2-l60OO/4R-15 dated 
18 June 1974. 



nNAL FLIGHT REPORT 



LTV-VSD-T Report No. 2-16000/4R-31 dtd 
20 Nov 1974; Rev. A, dted 19 Feb 1975 

VEHICLE SUCCESS RATIO SINCE RECERTIFICA TiON 



2M- 16000/4 L- 3930 dtd 26 June 197** 



TRANSMITTAL LETTER 



ir^f^maPH.i iv^w ^ki icrr 

2M-16000/4L-4643 dtd 26 November 1974 
2M-I6OOO/4L-3236 dtd 24 February 1975 



LAUNCH DATA 



ORIGINAL PAG£ IS 
458 OF POOR QUALITY 

TABLE CLXV- POSTFLIGHT SUMMARY, SCOUT S-187C 



SCOUT LAUNCH NO 

90 



LAUNCH T:ME (I.OCALI 



1047 



LAUNCH DATE 



13 October 1974 



LAUNCH S TE 



San Marco Platform, 
Kenya, Africa 



PAVLOAO TYPE 



UK- 5 



PAYLOAO WEIGHT 

■-« 288.35 



M.SS:ON TYPE 

1974 - 077A 



SCOUT MISSION 
TYPE NO 



72 



SUCCESS RAT O* 



64/67 - 0.955 



ct>UNTDOWN 



LAUNCH AZIMUTH (TRUE! 

90.0 


DEC 


LAUNCH ELEVATION. DEC 

90.0 


W NO DRECT ON DEG 

170 


W NO SPEED. KNOTS 

13 


RELATIVE HUMIDITY % 

71 


VISIBILITY, STATUTE MILES 

18.6 


TEMPERATURE. 'F 

79-5 


BAROMETER, 

1014.7 mb 


tke.ukn>ii 



CONFIGURATION 



HEA T SHIELD 



U2/-45, s/n A505 



SPIN MOTORS 



(4) 1.0KS75 



4TH-STAGE MODULE 
T/M S/N 009 



PIRst-STAGE MOTOR 

ALGOL lie 
S/N 79 



SECONO-STAGE MOTOR 



castor iia 
s/n 169 



THIRD-STAGE MOTOR 

ANTARES IIA 

s/n HiB-307 



FOURTH-STAGE MOTOR 

ALTAIR IIIA 
s/n TCC/E-13 



INST RUMEN TATION 



Standard PAM/FM/FM "D"-section and Uth-stage module telemetry systems. ISiere 
were six special temperature measxirements - 5 on 4th-stage and 1 on Base "A". 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjOj ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


270.16 


307.51 


+37.35 


2ND STAGE 
190.0 


3RD STAGE 
19.5 


PERIGEE,N. Ml. 


269.07 


271.07 


+2.00 


HjO, CONSUMED, LBS 


INCLINATION. DEG 


2.92 


2.86 


-0.06 


ZND-STAGE BOOST 
33.7 


3RD-STAGE BOOST 
1.5 


MAXIMUM VELOCITY 
FPS 


21*973.38 


25012.50 


+39.12 


2ND-STAGE COAST 
23.3 


3R0.4TAGE COAST 
1.7 


ALTITUDE. N. Ml. 


270.16 


27^^.13 


+3.97 




RETRO 

15-3 


SPIN RA TE 

AT SEPARATION 

RPM 


136.8 


136.3 


-0.5 ( 0.4 <f,) 


SPIN BEARING TORQUE. IN-LBS 
U6.3 


TELEMETRY COVERAGE 

Good T/m data was received thru 625 seconds by Santa Rita and from 65O to930 
seconds by the Seychelles receiving stations. Radar data was provided by the 
San Marco Range from 1.10 to 379-70 and 434.7 to ^3 '7 seconds flight time. 



REMARKS AND/OR ANOMALIES 



A voltage bias anomaly equiveJ-ent to the pitch down motor valve command 
fvinction occurred at 121.5 sec flight time. Vehicle motion indicated the 
problem was in the T/M system. At 3rd-stage ignition (155.1 sec), the 
telemetered signal returned to its normal level. 



)OCUMENTATION 



5 



X|nASA PREFLIGHT PLANNING REPORT 

AF FLIGHT TEST PLAN LTV-VSD-T Report No. 

2-I6OOO/UR-22 dated Ik August 1974, 
Revision A dated 3 October 1974 



TRANSMITTAL LETTER 



2M-16000/UL-4233 dtd 20 August 1974 
2M-16000/4L-44i8 dtd 8 October 197^ 



FINAL FLIGHT REPORT 



LTV-VSD Report No. 2-I6OOO/5R-7 dated 
7 May 1975 

VEHICLE SUCCESS RATIO SINCE REC E RTl Fl C A TION 



TRANSMITTAL LETTER 

2M-I6OOO/5L-3578 dtd 15 May 1975 



459 



ORIGINAL PAGE iS 
OF POOR QUALITY 



TABLE CLXVI - POSTFLIGHT SUMMARY, SCOUT S-188C 



LAUNCH DATA 

SCOUT LAUNCH NO. 



86 



LAUNCH TIME ILOCALI 

1922 PDT 



PA YLOAO TYPE 

(UK) X-k 



PAYLOAO WEIGHT 
LBS 



19 3-76 



LAUNCH DA TE 

8 March 197I+ 



;ss:ON TYPE 

197U - 01^ 



LAUNCH S TE 

SLC-5 VAFB, California 



SCOUT MISSION 
TYPE NO ,_ 

DO 



SUCCESS RAT.O* 



60/63 » 0.952U 



COUNTDOWN 

LAUNCH AZIMUTH (TRUE!. DEC 



192.157 



RELATIVE HUMIDITY 

79 

HEMAHKi 



LAUNCH ELEVATION. DEC 
90.0 



VISIBILITY. STATUTE MILES 

7 



WND DIRECT ON DEC 
326 



TEMPERATURE. "F 

hi 



W ND SPEED. KNOTS 
11 



BAROME TER,"HG 
29.550 



Coxmtdown #1 was aborted due to failure of pitch rate gyro (27 Feb.). The 
vehicle was laxmched 8 March with one hold encountered at T - 12 minutes due 
to Range clearance . 



CONFIGURATION 



^2/-1|5,S/n A5O6 



HEAT SHIELD 



FIRST-STA^e MOTOR 

AL50L IIIA 



SPIN MOTORS 



(2) 1.0KS75 and (2) LOKS^iO 



S/N 5502-7 



THIRD-STAGE MOTOR 

ANTARES IIA 



FOURTH-STAGE MOTOR 

ALTAIR IIIA 



SECOND-STAGE MOTOR 

castor iia 

s/n 198 

NSTRUMENTAT.oN Rad flrst of two "Add-On" 

ALGOL IIIA first-stage motor to have increased clearances between Jet vane 

bonnet and Base "A" flame barrier. 



s/n HiB-308 



^N HIB 

:m T/M 



4TH-STAQE MODULE 

T/M Yes 



s/n 2376-7 



systems . second scout with 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjO} ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


405.13 


501.31 


+96.18 


2ND STAGE 
183.0 


9RO STAGE 
19.4 


PERIGEE,N. Ml. 


404.97 


391.91 


-13.06 


HjOj CONSUMED, LBS 


INCLINATION. DEC 


98.40 


97.80 


-0.60 


2ND-STAGE BOOST 
43.5 


3RD-STAeE BOOST 
6.5 


MAXIMUM VELOCITY 
FPS 


24547.9 


24697.4 


+149.5 


2ND-STAGE COAST 
23.5 


3RO.9TA0E COAST 
1.2 


ALTITUDE. N. Ml. 


404.97 


402.06 


-2.91 




RETRO 

10.7 


SPIN RATE 

AT SEPARATION 

RPM 


154.9 


154.6 


-0.3 ( 0.2 i) 


SPIN BEARING TORQUE. IN-LBS 

64.1 


TELEMETRY COVERAGE ' 

VAFB auid Point Mugu receiving stations provided telemetry coverage thru 76O 
seconds of flight. Radar data were acquired by AN/rPS-lj6 at VAFB (Site l) 
and Pt. Mugu (Site 3) from T - O.33I* to T + 223.566 and T + 219.666 to T + 
645.066 seconds flight time, respectively. 



REMARKS AND/OR ANOMALIES 



All systems i>erformed as predicted with no anomalies noted. 



Rfi?H 



MENTATION 



f i- Arir^iri ^ MtKUW" 



^AF FLIGHT TEST PLAN LTV-VSD-T Report No. 
2-i6000/4r-2 dtd 10 January 1974, 
Revision A dated lU February 1971^ 

INAL FLIGHT REPORT rmir trOTN m n_ —4. »T, 



LTV-VSD-T Report No. 
2-I6OOO/UR-25 dated 23 September 1974 
Revision A dated 11 November 197^ 

VEHICLE SUCCESS RATIO SINCE REC E RT I Fl C A TION 



'KANSMitTAL LETTER 



2M-16000/4L- 301*6 dtd 14 January 1974 
2M-l6000/4L-3251 dtd 20 February 1974 



TRANSMITTAL LETTER 



2M-l6000/ltL-4376 dtd 27 September 197** 
2M-16000/4L-4631 dtd 21 November 1974 



TABLE CLXV 1 1 - 



LAUNCH DATA 



460 ORIGINAL P^^^^} 

OF POOR QViALO ^ 

POSTFLIGHT SUMMARY, SCOUT S-189C 



SCOUT LAUNCH NO 

89 



LAUNCH TIME ILOCALI 

0707 PPT 



LAUNCH DATE 

30 August 197'» 



LAUNCH S TE 

SLC-^ VAFB, California 



PA VLOAD TYPE 

AMS-A 



PAY LOA 
LBS 



EIGHT 

.01 



■i:SS:ON TYPE 

197*+ - 070A 



SCOUT MISSION 
TYPE NO '72_ 



SUCCESS RAT.O- 



63/66 - 0.95^5 



COUNTDOWN 



LAUNCH AZIMUTH (TRUE!. DEC 



191.88 



LAUNCH ELEVATION. DEC 



90.0 



ND DIRECT ON DEG 



3iH 



W NO SPEED KNOTS 



RELATIVE HUMIDITY % 

99 



VISIBILITY. STATUTE MILES 



TEMPERATURE. 'F 



lA 



55 



9AROMETER,"HG 
29.490 



Countdown #1 (27 August 197b) At T - 10 the payload unbillcal did not eject when coaawided. The uid>lllcal 
was co^MHded seversl tlaes and finally ejected. At T - 2 the sequencer stopped due to upper fin beiii« 
past l.J deg aaxlDum tolerance. Launch was aborted. Countdown fi (30 August 197^) Om hold in Tisk 7 
was encountered due to excessive open circuit voltage 00 destruct systea prior to aralng. 



CONFIGURATION 



}4/-40,S/N Ai^06 

FIRST-STAGE MOTOR 



HEA T SHIELD 



SPIN MOTORS 



(2) 1.0KS40 and (2) 1.0KS7^ 



THIRD-STAGE MOTOR 

ANTARES IIA 

s/n HiB-316 



4TH-STAGE MODULE 



ALGOL IIIA 
S/N ^^02-10 



SECOND-STAGE MOTOR 

CASTOR IIA 



S/n 201 



s/n tc/e-i4 



INSTRUMEN TATION 



First total PCM T/M system In fourth-stage module. Eight special temperature sensors were located in 
Base "A". First vehicle to use a Tliikol ALTAIR IIIA fourth-stage motor. 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 
PREDICTED 


H2O2 ON BOARD 

AT LIFT OFF 

LBS 


APOGEE, N. Ml. 


302.4 


63**. 3 


+331.9 


2ND STAGE 3RD STAGE 
183.0 18.8 


PERIGEEjN. Ml. 


275.2 


143.6 


-131.6 


H3O2 CONSUMED, LBS 


INCLINATION. DEO 


97.8 


98.04 


40.76 


2ND-STAGE BOOST 
33.1 


IRD-STACE BOOST 
5.2 


MAXIMUM VELOCITY 
FPS 


25003.5 


25792.0 


+788.5 


2ND-STAGE COAST 
22.7 


3RO-STACE COAST 
1.9 


ALTITUDE. N. Ml. 


275.25 


205.42 


-69.83 




RETRO 

10.8 


SPIN RATE 

AT SEPARATION 

RPM 


152.0 


152.1 


-K).l (0.06lt) 


SPIN BEARING TORQUE, IN-LBS 
^7.9 


TELEMETRY COVERAGE 

VAFB (IRS) received good "D"-Section to 610 sec and Uth-stage telemetry to J^ seconds fll^t time with 
some noise during third-stage bum. Ban Nicolas Island received good telemetry signal to ;$J and $40 
seconds flight time for "D'-sectlon and l»th-stage, respectively. Radar data were acquired by the AH/ 
FPS-16 at VAFB (Site 2) from T + 0.3 to T + 570.1 seconds flight time. 



REMARKS AND/OR ANOMALIES 



Ihree anomalies occurred during the flight: (l) the third pitch rate commaDd event (Oco) did not occur 
as prograoned; (2) the roll rate gyro was erratic during hi^ longitudinal acceleratioO porticos of 
second and thlrd-atage boost; and (3) third-stage retro occurred 7. 611 seconds later than programmed. 
Anomalies (l) and (3) were both related to a faulty Intervalometer and (2) was caused by a faulty gyro. 



)OCUMENTATION 



NASA PREFLIGHT PLANNING REPORT 

AF FLIGHT T«5T PLAN LTV-VSD-T Rcport No. 



2-16OOO/4R-2O dtd 26 July 197'+> 
Revision A dtd l8 September 197*^ 



FINAL FLIGHT REPORT iflY-YSD-T Report No . 
2-16OOO/5R-12 dated 7 April 1975 



TRANSMITTAL LETTER 



2M-16000/4L-4105 dtd 31 July 1971* 
2M-I6OOO/4L-4363 dtd 25 September 197** 



TRANSMITTAL LETTER 

2M-I6OOO/5L-343I dtd 10 April 1975 



VEHICLE SUCCESS RATIO SINCE REC E RTI Fl C A TION 



461 



OF POOR QUALITY 



LAUNCH DATA 

SCOUT LAUNCH kia. 



TABLE CLXVtII . - POSTFLIGHT SUMMARY, SCOUT S-I9OC 



85 



LAUNCH TIME (I.OCAI.I 
1305 



PAVLOAD TYPE 

San Marco C-2 



PAYLOAD WEIGHT 
'-'" 361.22 



LAUNCH DATE 



MISSION TYPE 

1974 - 009A 



18 February 197^^'K^ya7AgScg^°° ^^*^°"» 



SCOUT MISSION 
TYPE NO 



67 



SUCCESS RATIO- 



COUNTDOWN 



59/62 ■ 0.9516 



LAUNCH AZIMUTH (TRUE!. DEC 
90.0 



RELATIVE HUMIDITY. % 
, 71 

neMAKKs 



LAUNCH ELEVATION. DEC 
90.0 



vis:bility. statute miles 
21.7 



':nd directon dec 
OU5. 



TEMPERATURE. 'F 
81.1+ 



W NO SPEED. KNOTS 

9 



3AROMETER.-HG 
29.919 



Countdown was accomplished without any anomalies. A hold of 2 hours 
and 25 minutes was requested at T - 20 minutes due to weather conditions. 



CONFIGURATION 

HEAT SHIELD 

3V-25,s/n A-66 

PI HiT-iTAte l.toT6rt 

algol iiia 
s/n 5506-2 



SPIN MOTORS 



s/n 190 



(2) 1. 0KS75 a nd (2) 1.0KS40 

^HI^D-iTXie MOTOR 

ANTARES IIA 

s/n HiB-306 



SECOND-STAGE MOTOR 

CASTOR IIA 



4TH-STAGE MODULE 

T/M Yes 



s/n 2376-if 



UMENTAT.ON pij.g.(. s_Band "D"-Section and Fourth-Stage Module T/M. Special 
"D"-Section temperattare measurements were Base "A" Barrier and Fin 3 Actuator. 
F i ve temPftrnturft mftWRurements were 1nrAt.t»« ^ in kth-ntfute mndiils t /M- 



PERFORMANCE 



PARAMETER 



APOGEE, N. Ml. 



PERIGEEjN. Ml. 



INCLINATION, DEC 



MAXIMUM VELOCITY 
FPS 



ALTITUDE, N. Ml. 



SPIN RATE 

AT SEPARATION 

RPM 



PREDICTED 



458.87 



123.13 



2.92 



26051.2 



ACTUAL 



504.00 



125-55 



2.90 



26109.4 



123.13 



140.1 



TELEMETRY COVERA 



125.56 



DEVIATION 

FROM 

PREDICTED 



+45.13 



-H4.48 



-0.02 



+58.2 



143.3 



-H2.43 



HjO} ON BOARD 

AT LIFT OFF 

LBS 



2NO STAGE 
180.5 



3RD STAGE 
17.8 



H2O2 CONSUMED. LBS 



2ND-STAGE BOOST 
36.0 



ZNO-S-TAGE COAST 



CO. p 



3ROSTABE COAST 



3RD-STAGE BOOST 
3.7 



-STAB 

0.8 



RETRO 

12.3 



. ISPIN BEARING TORQUE, IN-LBS 

+3.2 ( 2.3i)\ 46.0 



The Santa Rita telemetry receiving station received good telemetry sigmal 
through fourth-stage burnout with no drop-outs. 



tEMARK^ AND/OR ANOMALIES 



All four stages indicated greater than predicted performance. 



DOCUMENTATION 



gl 
lASA PREFLIGHT PLANNING REPORT 
IF FLIGHT TEST PLAN LTV-VSD-T Rcport No . 
2-I6OOO/3R-51 dated 7 December 1973 
Revision A dated 3I January 1974 



iNAL FLIGHT REPORT ijv_vSD-T Report No. 
2-160OO/4R-16 dated 21 June 1974 



VEHICLE SUCCESS RATIO SINCE REC E R Tl FIC A TION 



TRANSMITTAL LETTER 



2M-I6OOO/3L-43II dtd 12 December I973 
2M-16000/4L-3171 dtd 1 February I974 



TRANSMITTAL LETTER 

2M-16000/4L-3944 dtd 28 June I974 



TABLE CLXU 



^2 oFpoORQUAUiY 

POSTFLIGHT SUMMARY, SCOUT S-191C 



LAUNCH DATA 



SCOUT LAUNCH NO 



87 



LAUNCH T:ME (LOCAL) 

1609 PDT 



LAUNCH DATE 

3 Jime 1974 



LAUNCH S TE 



SLC-5 VAFB, California 



PAYLOAD TYPE 

NIC HAWKEYE 



PAYLOAD WEIGHT 



58.56 



M.5S:ON TYPE 



SCOUT MISSION 
TYPE NO 



69 



SUCCESS RAT.O- 



61/64 - 0.9531 



COUNTDOWN 



LAUNtH izlMUTH (TRUE!. DEC 
182.076 


LAUNCH ELEVATION. DEC 
90.0 


WND DIRECT ON DEC 
340 


WND SPEED. KNOTS 

7 


RELATIVE MUMIDITV % 

88 


VISIBILITY, STATUTE MILES 

2 (Fog) 


TEMPERATURE. 'F 
55.0 


BAROMETER."HG 
29.62 


neuinxs — 
Coxintdown was normal with no major problems encountered. 



CONFIGURATION 



HEA T SHIELD 



SPIN MOTORS 



3V-J^0,S/n Ai^05 (2) 1.0KS75 and i^) l.OKS^O 

TIHiV-STAGE MOTOR ISECOND-STAGEMOTOR FI-'SS:? 



4TH-STAGE MODULE 

T/M Yes 



THIRO-STACE MOTO 

ANTARES IIB 
S/n HIB-iK)l 



5TH-STAGE T/M 

Yes 



algol iiia 
s/n 5502-8 



s/n 199 



s/n 2376-3 



INSTRUMENTATION ^^j.^ ^^^ ^j^^ Special temperature senaors and two vlbroaeter 
■ystems added to "D''-Sectlon T/m to monitor 3rd-8taee motor. 
Fourth-stage t/M included seven measurements for the Utb-stage 
ACS. The ^tb-atage T/h used the apacecraft antenna t> transmitter. 



FIFTH-STAGE MOTOR 

ALCYONE lA 

s/n AN09/003 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjOj ON BOARD 

AT LIFT OFF 

LBS 


*-rarfch radii 


15-993 


19-516 


+3.523 


2ND STAGE 
181.0 


3RD STAGE 
19.1 


PERIGEE, N. Ml. 


269-51 


252.28 


-17.23 


H2O2 CONSUMED, LBS 


INCLINATION. OEG 


90.0 


89.79 


-0.21 


ZND-STACE BOOST 

kk.3 


3RD-STAGE BOOST 
3.9 


MAXIMUM VELOCITY 
FPS 


3U229.26 


34U65.66 


+236.1+0 


2ND-STAGE COAST 

3^.8 


3RO-STAGE COAST 

1.8 


ALTITUDE. N. Ml. 


27'+.l*2 


262.21 


-12.21 




RETRO , 

12.4 


SPIN RATE 

AT SEPARATION 

RPM 


170.3 


169.5 


-0.8 ( 0.5 *) 


SPIN BEARING TORQUE. IN-LBS 

UO.O (Average) 


TELEMETRY COVERAGE 

Good T/M data vere received by VAFB (TBS) and San Nicolas Island for the "D'-Section and bth-Stage Nodul* 
to JJO and 370 seconds respectively. Tbe aircraft acquired data at 330, 3ltO and 350 seconds for tb* 3 
T/M systems and for Ittb aod Jth-stage T/H had good data to T > 1000 seconds flight tlma. I)a4ar data by 
AN/FFS-16 at VAFB (Site 2) Ms acquired from T 4- 3-$0 to T ■«■ ^30.00 seconds flight tla*. 



REMARKS AND/OR ANOMALIES 



Flfst time cooflguratloo ccaponents or arrangements were (l) Uth-stage Attitude Ccrrectlco S]rateB,(2) 
ADTAKES IIB 3Td-stage motor, (3) AI^rORB IIA (BB-3) Jth-atage motor, (li) 60-lb pitch and jraw ecntrol 
motors in "C" section, and new $tii-staga transition section. All vehicle syatasa perfoiaad as ex- 
pected except that Fin k appeared to have stalled at approximately 70 seconds flight time and tbe 
spin motion manltor failed to indicate relative motion between 3rd and Wtb-stagea. 



)OCUMENTATION 



Y^NASA PREFLIGHT PLANNING REPORT 

^AF FLIGHT TEST PLAN LTV-VSD-T Rcport No . 
2-16000/4R-8 dated 11 April 197**, Rev. 
A dtd 20 May & Rev. B dtd 29 May 197^ 



FINAL FLIGHT REPORT LTV-VSD-T Rcport No. 
2-I6OOO/UR-28 dated 5 November 197^, 
Revision A dated k February 1975 

VEHICLE SUCCESS RATIO SINCE REC E RTI FlC A TION 



TRANSMITTAL LETTER 



2M-16000/UL3U80 dtd I8 April 197't,2M- 

16000AL- 3657, 5/23/74 & 4l- 3786, 5/30/ 



'k 



TRANSMITTAL LETTER 



2M-I6OOO/I+L-U571 dtd 8 November 197** 
2M-I6000/5L-3185 dtd Ik February 1975 



%3 



LAUNCH DATA 



ORIGINAL PAQE m 
OF POOR QUALITY 
TABLE CLXX- POSTFLIGHT SUMMARY, SCOUT S-192C 



SCOUT LAUNCH NO 

102 



l-AUNCM T ME 'UOCAl.! 



2307 PDT 



LAUNCH DATE 

14 May 1981 



LAUNCH S TE 



SLV-5 VAFB, California 



PA YLOAD TV PE 



NOVA-1 



PAVLOAD WEIGHT 



365.11 



«:SS:ON TYPE 

198144a 



SCOUT MISSION 
TV PE NO 



83 



SUCCESS RA T.O- 



75/79 = 0.9494 



COUNTDOWN 



LAUNCH AZIMUTH (TRUEi. DEC 
182.10 


LAUNCH ELEVATION. DEC 
90.0 


WIND DIRECT-ON DEC 
360 


WND SPEED. KNOTS 

Ousting 20 l<nots 


RELATIVE HUMIDITY. % 

75 


VISIBILITY. STATUTE MILES 

7 


TEMPERATURE, 'F 
50.0 


BAROMETER."HC 
29.629 


— 


REMARKS 

Second flight of Antares IMA. 







CONFIGURATION 












HEA T SHIELD 

34-40 A-414 


SPIN MOTORS 

(2) 0.6KS40, (2) 1.0KS75 


••E" SEC TION T M 

"D" T/M 


F RST-STACE MOTOR 

ALGOL 1 1 lA 
S/N 5504-5 


S/N 385 


THIRD-STAGE MOTOR 

ANTARES IMA 
S/N E-2 


S/N E-25 


INSTRUMEN TATION 

Special instrumentation kit for Antares IMA. 



PERFORMANCE 



PARAMETER 


PREDICTED 


ACTUAL 


DEVIATION 

FROM 

PREDICTED 


HjOj ON BOARD 

AT LIFT OFF 

LBS 


APOGEE. N. Ml. 


951.6 


945.4 


-6.2 


2ND STAGE 

119.3 


3RD STAGE 

18.4 


PERICEEjN. Ml. 


369.5 


354.7 


-14.80 


HjOj CONSUMED, LBS 


INCLINATION, DEC 


90.01 


90.16 


.15 


2NO-STAGE BOOST 

34.9 


3RD-STAGE BOOST 

3.5 


MAXIMUM VELOCITY 
FPS 


25732.0 


25766.8 


34.8 


2ND-STAGE COAST 

17.7 


3RD-STAGE COAST 

2.0 


ALTITUDE. N. Ml. 


199.53 


191.82 


-7.71 




RETRO 

12.0 


SPIN RATE 

AT SEPARATION 

RPM 


135.7 


137.8 


2.1( 1.5 ^) 


SPIN BEARING TORQUE. IN-LBS 

43.1 


TELEMETRY COVERAGE ..«_.> .1 . -^ .^1 1 .. . _ . 7. 

VAFB was the primary site with secondary site at Point Mugu . 
An ARIA aircraft was also positioned at 6°16' N, 120°25.7' west for third 
and fourth stage coverage. FPS 16 at VAFB (site 023002) was the primary 
radar. Data required was usable but had to be hand faired due to obvious 
tracking errors . 



REMARKS AND/OR ANOMALIES 



Radar Beacon failed during second-stage coast (140 sec). 


Nozzle shield 


thermistor (third stage) failed during third-stage coast. 


Two of the four 


vibrometers experienced erratic behavior throughout the fl 


ight. Data also 


indicated vibrometer data on 203 may also be suspect. 





DOCUMENTATION 



K 

V 

1 


NASA PREFLIGHT PLANNING REPORT BrOChUrB 
AF FLIGHT TEST PLAN 

fought Corporation Report No. 2 
9200/1R-11 Dated April 20, 1981 


TRANSMITTAL LETTER 

2-19200/1 L-3291 Dated April 27, 1981 


FINAL FLIGHT REPORT 

Vought Corporation Report No. 2-19200/ 
1R-26, REV. A, Dated 11/11/81 


TRANSMITTAL LETTER 

2-19200/1 L-3621 Dated Oct. 1, I98I 
2-19200/1 L-3692 Dated Oct. 29, 1981 


• V 


EHICLE SUCCESS RATIO SINCE R E C E H T 1 Fl C A T ION 





kSk 



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SCOUT SECOND AND THIRD STAGES 



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